Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations 34871 

Service Bulletin 777–28–0078, Revision 1, 

dated April 27, 2015, concurrently with 

accomplishing the actions required by 

paragraph (g) of this AD, install a new P301 

panel on the left side of the airplane, install 

a new P302 panel on the right side of the 

airplane, and change the wiring; or perform 

bonding resistance measurements and rework 

the airplane installations; as applicable; in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 777– 

28A0047, Revision 5, dated September 20, 

2010; or Boeing Service Bulletin 777– 

28A0047, Revision 6, dated July 11, 2013. 

(2) For airplanes identified in Boeing 

Special Attention Service Bulletin 777–28– 

0078, Revision 1, dated April 27, 2015, 

except for Group 10 airplanes on which the 

actions described in Boeing Service Bulletin 

777–28–0060; or Work Package 2 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–28–0062, have not been 

accomplished: Concurrently with 

accomplishing the requirements of paragraph 

(g) of this AD, do wiring changes in the P110 

and P210 panels, in accordance with the 

applicable Accomplishment Instructions of 

GE Aviation Service bulletin 5000ELM–28– 

075, Revision 1, dated August 5, 2014; and 

GE Aviation Service Bulletin 6000ELM–28– 

076, Revision 1, dated August 5, 2014. 

(i) Parts Installation Prohibition 

For Group 10 airplanes, as identified in 

Boeing Special Attention Service Bulletin 

777–28–0078, Revision 1, dated April 27, 

2015, after completion of the actions required 

by paragraph (g) of this AD, no person may 

install an auxiliary fuel tank on any Group 

10 airplane. 

(j) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (h)(1) of this 

AD, if those actions were performed before 

May 26, 2011 (the effective date of AD 2011– 

09–05, Amendment 39–16667 (77 FR 22305, 

April 21, 2011)), using a service bulletin 

identified in paragraph (j)(1)(i) or (j)(1)(ii) of 

this AD, which are not incorporated by 

reference in this AD. 

(i) Boeing Service Bulletin 777–28A0047, 

Revision 3, dated June 11, 2009. 

(ii) Boeing Service Bulletin 777–28A0047, 

Revision 4, dated May 20, 2010. 

(2) This paragraph provides credit for 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Special 

Attention Service Bulletin 777–28–0078, 

dated September 4, 2014, which is not 

incorporated by reference in this AD. 

(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, 

modification, or alteration 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. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane and the 

approval must specifically refer to this AD. 

(4) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (k)(4)(i) and (k)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(l) Related Information 

(1) For more information about this AD, 

contact Sue Lucier, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6438; fax: 425– 

917–6590; email: suzanne.lucier@faa.gov. 

(2) Boeing service information identified in 

this AD that is not incorporated by reference 

is available at the addresses specified in 

paragraphs (m)(3) and (m)(5) 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 Service Bulletin 777–28A0047, 

Revision 5, dated September 20, 2010. 

(ii) Boeing Service Bulletin 777–28A0047, 

Revision 6, dated July 11, 2013. 

(iii) Boeing Special Attention Service 

Bulletin 777–28–0078, Revision 1, dated 

April 27, 2015. 

(iv) GE Aviation Service Bulletin 

5000ELM–28–075, Revision 1, dated August 

5, 2014. 

(v) GE Aviation Service Bulletin 6000ELM– 

28–076, Revision 1, dated August 5, 2014. 

(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) For GE Aviation service information 

identified in this AD, contact GE Aviation 

Fleet Support, 1 Neumann Way, Cincinnati, 

OH 45215; telephone 513–552–3272; email: 

aviation.fleetsupport@ge.com; Internet http:// 

www.geaviation.com. 

(5) 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. 

(6) 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 May 18, 

2016. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–12443 Filed 5–31–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–5812; Directorate 

Identifier 2015–NM–077–AD; Amendment 

39–18531; AD 2016–11–04] 

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) 2011–23– 

05 for all The Boeing Company Model 

737–300, –400, and –500 series 

airplanes. AD 2011–23–05 required 

repetitive inspections for cracking of the 

1.04-inch nominal diameter wire 

penetration hole, and applicable related 

investigative and corrective actions. 

This new AD adds new inspection 

areas, a modification that terminates 

certain inspections, post-modification 

inspections, and repair if necessary. 

This AD was prompted by an evaluation 

by the design approval holder (DAH) 

that indicates the fuselage frames and 

frame reinforcements are subject to 

widespread fatigue damage (WFD). We 

are issuing this AD to detect and correct 

fatigue cracking of the fuselage frames 

and frame reinforcements that could 


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34872 Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations 

result in reduced structural integrity of 

the airplane. 

DATES: This AD is effective July 6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of November 16, 2011 (76 FR 

67343, November 1, 2011). 

ADDRESSES: For service information 

identified in this final rule, 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 this 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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

5812. 

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–2015– 

5812; 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: 

Galib Abumeri, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 

562–627–5324; fax: 562–627–5210; 

email: galib.abumeri@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2011–23–05, 

Amendment 39–16856 (76 FR 67343, 

November 1, 2011) (‘‘AD 2011–23–05’’). 

AD 2011–23–05 applied to certain 

Model 737–300, –400, and –500 series 

airplanes. The NPRM published in the 

Federal Register on November 27, 2015 

(80 FR 74047) (‘‘the NPRM’’). The 

NPRM was prompted by an evaluation 

by the DAH that indicates the fuselage 

frames and frame reinforcements are 

subject to WFD. The NPRM proposed to 

continue to require repetitive 

inspections for cracking of the 1.04-inch 

nominal diameter wire penetration hole, 

and applicable related investigative and 

corrective actions. The NPRM also 

proposed to add new inspection areas, 

a modification that terminates certain 

inspections, post-modification 

inspections, and repair if necessary. We 

are issuing this AD to detect and correct 

fatigue cracking of the fuselage frames 

and frame reinforcements that could 

result in reduced structural integrity of 

the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

accomplishing the supplemental type 

certificate (STC) ST01219SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

ebd1cec7b301293e86257cb30045557a/

$FILE/ST01219SE.pdf) does not affect 

the actions specified in the NPRM. 

We agree with the commenter. We 

have redesignated paragraph (c) of the 

proposed AD as paragraph (c)(1) and 

added a 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/

ebd1cec7b301293e86257cb30045557a/

$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. 

Request To Revise Applicability 

Boeing requested that we change the 

applicability to ‘‘all’’ airplanes instead 

of airplanes referenced in Boeing Alert 

Service Bulletin 737–53A1279, Revision 

2, dated April 21, 2015. Boeing stated 

that Boeing Alert Service Bulletin 737– 

53A1279, Revision 2, dated April 21, 

2015, specifies the effectivity as ‘‘all’’ 

airplanes. 

We agree with the commenter’s 

request. In the NPRM we referred to 

Boeing Alert Service Bulletin 737– 

53A1279, Revision 2, dated April 21, 

2015, which specifies an effectivity of 

all Model 737–300, –400, and –500 

series airplanes. For clarity, we have 

revised the SUMMARY section and 

paragraph (c)(1) of this AD to specify 

‘‘all’’ airplanes. 

Request To Revise Compliance Time 

Southwest Airlines (SWA) requested 

that we revise paragraph (t) of the 

proposed AD to clearly state all 

inspections required by paragraph (n) of 

the proposed AD will be due at the later 

of 30,000 total flight cycles or 4,500 

flight cycles from the effective date of 

the AD. SWA stated that, for airplanes 

which have previously accomplished 

the inspections specified in Boeing 

Alert Service Bulletin 737–53A1279, 

Revision 1, dated September 2, 2011, 

paragraph (n) of the proposed AD and 

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

in Boeing Alert Service Bulletin 737– 

53A1279, Revision 2, dated April 21, 

2015, currently requires inspections 

4,500 flight cycles from the last 

inspection and do not specifically take 

into account those airplanes already 

doing the repetitive inspections. 

We do not agree with the commenter’s 

request. AD 2011–23–05 required 

inspections on airplanes with less than 

40,000 total flight cycles to begin prior 

to 30,000 total flight cycles or within 90 

days from November 16, 2011 (the 

effective date of AD 2011–23–05), 

whichever occurs later. The repetitive 

inspection intervals of 4,500 flight 

cycles are not changed. The new WFD 

requirement lowers the initial airplane 

applicability total flight cycles from 

40,000 to 30,000. Paragraph (n) of this 

AD addresses airplanes with more than 

30,000 total flight cycles as of the 

effective date of the AD, and all 

airplanes that have already 

accomplished the initial inspection or a 

repetitive inspection. These airplanes 

are to continue the repetitive 

inspections at intervals not to exceed 

4,500 flight cycles from the last 

inspection. The commenter’s requested 

change would reset the time to the next 

inspection from the effective date of this 

AD instead of from the last inspection. 

This would result in a one-time increase 

in the repetitive interval, which would 

not meet the WFD requirements. We 

have not changed this AD in this regard. 

Request To Clarify Inspections in 

Paragraphs (m) and (n) of the Proposed 

AD 

Boeing requested that we clarify the 

inspections required in paragraph (m) 


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Federal Register / Vol. 81, No. 105 / Wednesday, June 1, 2016 / Rules and Regulations 34873 

and (n) of the proposed AD. Boeing 

stated that the words ‘‘an inspection’’ is 

not specific enough to ensure the 

required inspections will be 

accomplished. 

We agree with the commenter’s 

request. The wording ‘‘an inspection’’ 

could be interpreted incorrectly, and the 

Part 2 or Part 4 inspections specified in 

Boeing Alert Service Bulletin 737– 

53A1279, Revision 2, dated April 21, 

2015, may not be accomplished prior to 

installation of the preventive 

modification. 

We have revised paragraph (m) of this 

AD to state in part, ‘‘before further flight 

after accomplishing the Part 2 or Part 4 

inspections specified in this paragraph, 

and no cracking was found, do ‘‘Part 5— 

Preventative Modification’’ as specified 

in the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737– 

53A1279, Revision 2, dated April 21, 

2015.’’ 

We have revised paragraph (n) of this 

AD to state in part, ‘‘before further flight 

after accomplishing the Part 4 

inspection specified in this paragraph, 

and no cracking was found, do ‘‘Part 5— 

Preventative Modification’’ as specified 

in the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737– 

53A1279, Revision 2, dated April 21, 

2015.’’ 

Request To Remove a Certain Low 

Frequency Eddy Current (LFEC) 

Inspection 

Boeing requested that we remove the 

LFEC inspection in paragraph (s) of the 

proposed AD. Boeing stated that 

paragraph (s) of the proposed AD is 

applicable to Groups 4 through 6 as 

identified in Boeing Alert Service 

Bulletin 737–53A1279, Revision 2, 

dated April 21, 2015, and that LFEC 

inspections are not required for Groups 

4 through 6. 

We agree with the commenter’s 

request. We have revised paragraph (s) 

of this AD by removing the LFEC 

inspection requirement. 

Request To Clarify Service Information 

Description 

Boeing requested that we include 

‘‘0.50 inch diameter holes’’ in the first 

bullet under the Related Service 

Information Under 1 CFR part 51 

section. Boeing stated that the 0.50 inch 

hole was one of the main updates of 

Boeing Alert Service Bulletin 737– 

53A1279, Revision 2, dated April 21, 

2015. 

We agree with commenter’s request 

and have revised this final rule 

accordingly. 

Request To Revise Responsible FAA 

ACO 

Boeing requested that we revise 

paragraph (u)(3) of the proposed AD to 

reference the Los Angeles ACO instead 

of the Seattle ACO. 

We agree with the commenter’s 

request. In July 2014, the Los Angeles 

ACO assumed responsibility for the outof-production Model 737 airplanes. We 

have revised paragraph (u)(3) of this AD 

and the engineer contact information 

accordingly. 

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 for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 737–53A1279, Revision 2, 

dated April 21, 2015. The service 

information describes procedures for the 

following actions. 

• Inspections of wire penetration 

holes, 0.50 inch diameter holes, 

standoff/tooling holes, and the 

production fastener holes for cracking in 

the forward cargo compartment frames 

and frame reinforcements, between 

stringer (S) S–19 and S–22, on both left 

and right sides of the airplane. 

• A preventive modification of frames 

between S–19 and S–22. 

• Post-modification inspections. 

• Repairs. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 605 

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 actions from AD 

2011–23–05].

16 work-hours × $85 per hour = $1,360 

per inspection cycle.

$0 $1,360 per inspection cycle.$822,800 per inspection cycle. 

Inspections [new action] ......................... 32 work-hours × $85 per hour = $2,720 

per inspection cycle.

0 $2,720 per inspection cycle.$1,645,600 per inspection cycle. 

Modification [new action] ........................ 32 work-hours × $85 per hour = $2,720 0 $2,720 .................... $1,645,600 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Repair .............................................. 18 work-hours × $85 per hour = $1,530 ................................................... $0 $1,530 


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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) 

2011–23–05, Amendment 39–16856 (76 

FR 67343, November 1, 2011), and 

adding the following new AD: 

2016–11–04 The Boeing Company: 

Amendment 39–18531; Docket No. 

FAA–2015–5812; Directorate Identifier 

2015–NM–077–AD. 

(a) Effective Date 

This AD is effective July 6, 2016. 

(b) Affected ADs 

This AD replaces AD 2011–23–05, 

Amendment 39–16856 (76 FR 67343, 

November 1, 2011) (‘‘AD 2011–23–05’’). 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 737–300, –400, and –500 

series airplanes; certificated in any category. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

ebd1cec7b301293e86257cb30045557a/$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 an evaluation by 

the design approval holder (DAH) that 

indicates the fuselage frames and frame 

reinforcements are subject to widespread 

fatigue damage (WFD). We are issuing this 

AD to detect and correct fatigue cracking of 

the fuselage frames and frame 

reinforcements, which could result in 

reduced structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection, With References to 

Terminating Actions 

This paragraph restates the requirements of 

paragraph (g) of AD 2011–23–05, with 

references to terminating actions. At the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1279, Revision 1, dated 

September 2, 2011, except as required by 

paragraphs (k)(1), (k)(2), and (k)(4) of this AD: 

Do a high frequency eddy current (HFEC) 

surface or HFEC hole/edge inspection for any 

cracking of the 1.04-inch nominal diameter 

wire penetration hole in the frame and frame 

reinforcement between stringer (S) S–20 and 

S–21, in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1279, Revision 1, 

dated September 2, 2011. Accomplishment of 

the applicable inspections required by 

paragraphs (m) and (n) of this AD terminates 

the inspections required by this paragraph. 

Accomplishment of the modification 

required by paragraph (p) of this AD 

terminates the inspections required by this 

paragraph for the modified area only. 

(h) Retained Repetitive Inspections, With 

References to Terminating Actions 

This paragraph restates the requirements of 

paragraph (h) of AD 2011–23–05, with 

references to terminating actions. Within 

4,500 flight cycles after accomplishment of 

the most recent inspection specified in Part 

2 or Part 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1279, Revision 1, dated September 

2, 2011, or within 90 days after November 16, 

2011 (the effective date of AD 2011–23–05), 

whichever occurs later: Do an HFEC hole/

edge inspection for cracking of the 1.04-inch 

nominal diameter wire penetration hole in 

the frame and frame reinforcement between 

S–20 and S–21, in accordance with Part 4 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–53A1279, 

Revision 1, dated September 2, 2011. Repeat 

the inspection thereafter at intervals not to 

exceed 4,500 flight cycles. Accomplishment 

of the applicable inspections required by 

paragraphs (m) and (n) of this AD, terminates 

the inspections required by this paragraph. 

Accomplishment of the modification 

specified in paragraph (j) or (p) of this AD 

terminates the repetitive inspections required 

by this paragraph for the modified area only. 

Accomplishment of the repair specified in 

paragraph (i) of this AD terminates the 

repetitive inspections required by this 

paragraph for the repaired area only. 

(i) Retained Repair, With No Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–23–05, with no 

changes. If any cracking is found during any 

inspection required by paragraph (g) or (h) of 

this AD: Before further flight, repair the crack 

including doing all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1279, Revision 1, dated September 

2, 2011, except as required by paragraph 

(k)(3) of this AD. All applicable related 

investigative and corrective actions must be 

done before further flight. Accomplishment 

of the requirements of this paragraph 

terminates the repetitive inspection 

requirements of paragraph (h) of this AD for 

the repaired location of that frame. 

(j) Retained Optional Terminating Action, 

With New Limitation 

This paragraph restates the optional action 

provided in paragraph (j) of AD 2011–23–05, 

with a new limitation. Accomplishment of 

the preventive modification before the 

effective date of this AD, including doing all 

related investigative and applicable 

corrective actions, specified in Part 5 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1279, Revision 1, 

dated September 2, 2011, except as required 

by paragraph (k)(3) of this AD, terminates the 

repetitive inspection requirements of 

paragraph (h) of this AD for the modified 


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location of that frame, provided the 

modification is done before further flight 

after an inspection required by paragraph (g) 

or (h) of this AD has been done, and no 

cracking was found on that frame location 

during that inspection. 

(k) Retained Exceptions to Service 

Information Specifications, With No 

Changes 

This paragraph restates the requirements of 

paragraph (k) of AD 2011–23–05, with no 

changes. The following exceptions apply as 

specified in paragraphs (g), (i), and (j) of this 

AD. 

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

Boeing Alert Service Bulletin 737–53A1279, 

Revision 1, dated September 2, 2011, refers 

to a compliance time ‘‘from date on Revision 

1 of this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after November 16, 2011 (the effective 

date of AD 2011–23–05). 

(2) For airplanes meeting all of the criteria 

specified in paragraphs (k)(2)(i), (k)(2)(ii), 

and (k)(2)(iii) of this AD: The compliance 

time for the initial inspection specified in 

Part 2 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1279, 

Revision 1, dated September 2, 2011, and 

required by paragraph (g) of this AD, may be 

extended to 90 days after November 16, 2011 

(the effective date of AD 2011–23–05). 

(i) Model 737–300 series airplanes in 

Group 1, line numbers 1001 through 2565 

inclusive; 

(ii) Airplanes that have accumulated 

40,000 or more total flight cycles as of 

November 16, 2011 (the effective date of AD 

2011–23–05); and 

(iii) Airplanes on which the modification 

specified in Boeing Service Bulletin 737–53– 

1273, dated September 20, 2006; Revision 1, 

dated December 21, 2006; Revision 2, dated 

June 4, 2007; Revision 3, dated December 7, 

2009; or Revision 4, dated July 23, 2010; has 

been done, including any configuration or 

deviation that has been approved as an 

AMOC during accomplishment of these 

service bulletins, by the Boeing Commercial 

Airplanes Organization Designation 

Authorization (ODA) that has been 

authorized by the Manager, Seattle Aircraft 

Certification Office (ACO) or Los Angeles 

ACO to make those findings. 

(3) Where Boeing Alert Service Bulletin 

737–53A1279, Revision 1, dated September 

2, 2011, specifies to contact Boeing for 

appropriate repair instructions: Before 

further flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (u) of this AD. 

(4) The ‘‘Condition’’ column of paragraph 

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

Bulletin 737–53A1279, Revision 1, dated 

September 2, 2011, refers to total flight cycles 

‘‘at the date of/on this service bulletin.’’ 

However, this AD applies to the airplanes 

with the specified total flight cycles as of 

November 16, 2011 (the effective date of AD 

2011–23–05). 

(l) Retained Credit for Previous Actions, 

With No Changes 

This paragraph restates the requirements of 

paragraph (l) of AD 2011–23–05, with no 

changes. Actions done in accordance with 

Boeing Alert Service Bulletin 737–53A1279, 

dated December 18, 2007, before November 

16, 2011 (the effective date of AD 2011–23– 

05), are acceptable for compliance with the 

corresponding actions required by 

paragraphs (g), (h), (i), and (j) of this AD. 

(m) New Requirement of This AD: 

Inspections of Frames and Frame 

Reinforcements Between S–19 and S–22 for 

Certain Airplanes on Which Certain 

Inspections Have Not Been Accomplished 

For airplanes identified as Groups 1 

through 6, Configuration 3, in Boeing Alert 

Service Bulletin 737–53A1279, Revision 2, 

dated April 21, 2015, with 30,000 total flight 

cycles or fewer as of the effective date of this 

AD, on which any inspections specified in 

Boeing Alert Service Bulletin 737–53A1279, 

Revision 1, dated September 2, 2011, have 

not been accomplished: Except as required 

by paragraphs (t)(1) and (t)(2) of this AD, at 

the applicable time specified in table 1 of 

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

Alert Service Bulletin 737–53A1279, 

Revision 2, dated April 21, 2015, or within 

4,500 flight cycles after the effective date of 

this AD, whichever occurs later, do 

inspections for cracking at certain locations 

in the frames and frame reinforcements in 

accordance with ‘‘Part 2—Initial Detail and 

HFEC Inspection’’ of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1279, Revision 2, dated April 21, 

2015. Repeat the inspections for cracking at 

certain locations in the frames and frame 

reinforcements as specified in ‘‘Part 4— 

Repeat Detail and HFEC Inspections’’ of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1279, Revision 2, 

dated April 21, 2015, thereafter at the 

applicable interval specified in paragraph 

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

Bulletin 737–53A1279, Revision 2, dated 

April 21, 2015; or, before further flight after 

accomplishing the Part 2 or Part 4 

inspections specified in this paragraph, and 

no cracking was found, do ‘‘Part 5— 

Preventative Modification’’ as specified in 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–53A1279, 

Revision 2, dated April 21, 2015. 

Accomplishment of the preventive 

modification specified in this paragraph 

terminates the repetitive inspections required 

by this paragraph for the modified area only. 

Do all actions specified in this paragraph in 

accordance with Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1279, Revision 2, dated April 21, 

2015. 

(n) New Requirement of This AD: 

Inspections of Frames and Frame 

Reinforcements Between S–19 and S–22 for 

Groups 1–6, Configuration 3, Airplanes 

For airplanes identified as Groups 1 

through 6, Configuration 3, in Boeing Alert 

Service Bulletin 737–53A1279, Revision 2, 

dated April 21, 2015, with more than 30,000 

total flight cycles as of the effective date of 

this AD, or that have been inspected as 

specified in Boeing Alert Service Bulletin 

737–53A1279, Revision 1, dated September 

2, 2011: Except as required by paragraphs 

(t)(1) and (t)(2) of this AD, at the applicable 

time specified in table 1 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1279, Revision 2, dated 

April 21, 2015, do inspections for cracking at 

certain locations of the frames and frame 

reinforcements in accordance with ‘‘Part 4— 

Repeat Detail and HFEC Inspections’’ of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1279, Revision 2, 

dated April 21, 2015. Repeat the inspections 

thereafter at the applicable interval specified 

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

Alert Service Bulletin 737–53A1279, 

Revision 2, dated April 21, 2015; or, before 

further flight after accomplishing the Part 4 

inspection specified in this paragraph, and 

no cracking was found, do ‘‘Part 5— 

Preventative Modification’’ as specified in 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–53A1279, 

Revision 2, dated April 21, 2015. 

Accomplishment of the preventive 

modification specified in this paragraph 

terminates the repetitive inspections required 

by this paragraph for the modified area only. 

(o) New Requirement of This AD: Repairs 

If any crack is found during any inspection 

required by paragraph (m) or (n) of this AD: 

Before further flight, repair, in accordance 

with ‘‘Part 3—Repair’’ of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1279, Revision 2, 

dated April 21, 2015, except where Boeing 

Alert Service Bulletin 737–53A1279, 

Revision 2, dated April 21, 2015, specifies to 

contact Boeing for damage removal and 

repair instructions, repair before further 

flight using a method approved in 

accordance with the procedures specified in 

paragraph (u) of this AD. Accomplishing a 

repair terminates the inspections required by 

paragraphs (m) and (n) of this AD in the 

repaired area only. Accomplishment of a 

repair terminates the modification required 

by paragraph (p) of this AD at the repaired 

location only. 

(p) New Requirement of This AD: 

Preventative Modification of the Frames 

Between S–19 and S–22 

For airplanes identified as Groups 1 

through 6, Configuration 3, in Boeing Alert 

Service Bulletin 737–53A1279, Revision 2, 

dated April 21, 2015: Except as required by 

paragraphs (t)(1) and (t)(2) of this AD, at the 

applicable time specified in table 2 of 

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

Alert Service Bulletin 737–53A1279, 

Revision 2, dated April 21, 2015, do the 

preventive modification of the frames 

between S–19 and S–22, in accordance with 

‘‘Part 5—Preventative Modification’’ of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1279, Revision 2, 

dated April 21, 2015. Accomplishment of the 

modification required by this paragraph 

terminates the requirements of paragraphs 

(g), (h), (m), and (n) of this AD for the 

modified location only. 

(q) New Requirement of This AD: 

Inspections of Preventive Modification for 

Groups 1–3, Configuration 1, Airplanes 

For airplanes identified as Groups 1 

through 3, Configuration 1, in Boeing Alert 


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Service Bulletin 737–53A1279, Revision 2, 

dated April 21, 2015: Except as required by 

paragraph (t)(1) of this AD, at the applicable 

time specified in table 3 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1279, Revision 2, dated 

April 21, 2015, do HFEC, LFEC, and detailed 

inspections for cracking in accordance with 

‘‘Part 7—INSPECTION OF PREVENTATIVE 

MODIFICATION’’ of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1279, Revision 2, dated April 21, 

2015. Repeat the inspections thereafter at the 

applicable interval specified in paragraph 

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

Bulletin 737–53A1279, Revision 2, dated 

April 21, 2015. If any cracking is found 

during any inspection required by this 

paragraph, before further flight, repair using 

a method approved in accordance with the 

procedures specified in paragraph (u) of this 

AD. 

(r) New Requirement of This AD: Inspections 

of Preventive Modification for Groups 1–6, 

Configuration 2, Airplanes 

For airplanes identified as Groups 1 

through 6, Configuration 2, in Boeing Alert 

Service Bulletin 737–53A1279, Revision 2, 

dated April 21, 2015: Except as required by 

paragraph (t)(1) of this AD, at the applicable 

time specified in table 4 or table 6 of 

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

Alert Service Bulletin 737–53A1279, 

Revision 2, dated April 21, 2015, do HFEC, 

LFEC, and detailed inspections for cracking 

in accordance with ‘‘Part 8—INSPECTION 

OF PREVENTATIVE MODIFICATION’’ of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1279, Revision 2, 

dated April 21, 2015. Repeat the inspections 

thereafter at the applicable interval specified 

in table 4 or table 6 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1279, Revision 2, dated 

April 21, 2015. If any cracking is found 

during any inspection required by this 

paragraph, before further flight, repair using 

a method approved in accordance with the 

procedures specified in paragraph (u) of this 

AD. 

(s) New Requirement of This AD: Inspections 

of Preventive Modification for Groups 4–6, 

Configuration 1, Airplanes 

For airplanes identified as Groups 4 

through 6, Configuration 1, in Boeing Alert 

Service Bulletin 737–53A1279, Revision 2, 

dated April 21, 2015: At the applicable time 

specified in table 5 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1279, Revision 2, dated 

April 21, 2015, except as required by 

paragraph (t)(1) of this AD: Do HFEC and 

detailed inspections for cracking in 

accordance with ‘‘Part 7—INSPECTION OF 

PREVENTATIVE MODIFICATION’’ of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1279, Revision 2, 

dated April 21, 2015. Repeat the inspections 

thereafter at the applicable time specified in 

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

Alert Service Bulletin 737–53A1279, 

Revision 2, dated April 21, 2015. If any 

cracking is found during any inspection 

required by this paragraph, before further 

flight, repair using a method approved in 

accordance with the procedures specified in 

paragraph (u) of this AD. 

(t) New Requirement of This AD: Exceptions 

to Service Bulletin Specifications 

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

Boeing Alert Service Bulletin 737–53A1279, 

Revision 2, dated April 21, 2015, refers to a 

compliance time ‘‘after the Revision 2 date of 

this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(2) The ‘‘Condition’’ column in table 1 and 

table 2 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1279, 

Revision 2, dated April 21, 2015, refers to 

total flight cycles ‘‘at the Revision 2 date of 

this service bulletin.’’ However, this AD 

applies to the airplanes with the specified 

total flight cycles as of the effective date of 

this AD. 

(u) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 (v)(1) of this AD. Information may 

be emailed to: 9-ANM-LAACO-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, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes ODA that has been 

authorized by the Manager, Los Angeles 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for the ADs in 

paragraphs (u)(4)(i) through (u)(4)(iii) of this 

AD are approved as AMOCs for the 

corresponding provisions of this AD. 

(i) AD 2009–02–06, Amendment 39–15796 

(74 FR 10469, March 11, 2009). 

(ii) AD 2009–02–06 R1, Amendment 39– 

16015 (74 FR 45979, September 8, 2009). 

(iii) AD 2011–23–05. 

(v) Related Information 

(1) For more information about this AD, 

contact Galib Abumeri, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles ACO, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5324; fax: 562–627–5210; email: 

galib.abumeri@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(w) 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 July 6, 2016. 

(i) Boeing Alert Service Bulletin 737– 

53A1279, Revision 2, dated April 21, 2015. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on November 16, 2011 (76 

FR 67343, November 1, 2011). 

(i) Boeing Alert Service Bulletin 737– 

53A1279, Revision 1, dated September 2, 

2011. 

(ii) Reserved. 

(5) 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. 

(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 May 18, 

2016. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–12329 Filed 5–31–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8465; Directorate 

Identifier 2014–NM–239–AD; Amendment 

39–18535; AD 2016–11–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Defense and Space S.A. (Formerly 

Known as Construcciones 

Aeronauticas, S.A.) 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2001–12– 


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