Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations 72511 

TABLE 1 TO PARAGRAPH (j)(4) OF THIS

AD—ASM REPLACEMENT—Continued 

Affected airplane 

configuration ASM part No. 

Post-Airbus Service Bulletin 

A320–47–1011 .................. 2060017–102 

(k) Retained Requirement: No Alternative 

Actions, Intervals, and/or CDCCLs, With No 

Changes 

This paragraph restates the requirements of 

paragraph (k) of AD 2012–20–07, with no 

changes. Except as required by paragraph (l) 

of this AD, after accomplishing the revisions 

required by paragraph (j) of this AD, no 

alternative actions (e.g., inspections), 

intervals, and/or CDCCLs may be used other 

than those specified in Airbus A318/A319/ 

A320/A321 ALS Part 5—Fuel Airworthiness 

Limitations, dated February 28, 2006, as 

defined in Airbus A318/A319/A320/A321 

Fuel Airworthiness Limitations, Document 

95A.1931/05, Issue 4, dated August 26, 2010, 

unless the actions, intervals, and/or CDCCLs 

are approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (n)(1) of 

this AD. 

(l) New Requirement of This AD: Revise the 

Maintenance or Inspection Program 

Within 60 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, by incorporating the 

fuel airworthiness limitations (e.g., life 

limits, tasks, and CDCCLs, and associated 

thresholds and intervals) described in Airbus 

A318/A319/A320/A321 ALS Part 5, Fuel 

Airworthiness Limitations, Revision 01, 

dated July 9, 2014. The initial compliance 

times for the tasks are at the times specified 

in Airbus A318/A319/A320/A321 ALS Part 

5, Fuel Airworthiness Limitations, Revision 

01, dated July 9, 2014, or within 60 days after 

the effective date of this AD, whichever 

occurs later. Incorporating the requirements 

of this paragraph terminates the requirements 

of paragraphs (g) through (k) of this AD. 

(m) New Requirement of This AD: No 

Alternative Actions, Intervals, or CDCCLs 

After the maintenance or inspection 

program has been revised as required by 

paragraph (l) of this AD, no alternative 

actions (e.g., inspections), intervals, or 

CDCCLs may be used unless the actions, 

intervals, or CDCCLs are approved as an 

AMOC in accordance with the procedures 

specified in paragraph (n)(1) of this AD. 

(n) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 

(i) 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. 

(ii) AMOCs approved previously for AD 

2012–20–07 are approved as AMOCs for the 

corresponding provisions of this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, 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 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0260, dated 

December 5, 2014, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2016–5589. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (p)(7) and (p)(8) of this AD. 

(p) 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. 

(3) The following service information was 

approved for IBR on November 25, 2016. 

(i) Airbus A318/A319/A320/A321 

Airworthiness Limitations Section (ALS) Part 

5, Fuel Airworthiness Limitations, Revision 

01, dated July 9, 2014. The title page of this 

document does not contain the revision date. 

The remaining pages of this document do not 

include the revision level. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on November 21, 2012 (77 

FR 63716, October 17, 2012). 

(i) Airbus A318/A319/A320/A321 Fuel 

Airworthiness Limitations, Document 

95A.1931/05, Issue 4, dated August 26, 2010. 

(ii) Reserved. 

(5) The following service information was 

approved for IBR on December 14, 2009 (74 

FR 62219, November 27, 2009). 

(i) Airbus A318/A319/A320/A321 Fuel 

Airworthiness Limitations, Document 

95A.1931/05, Issue 2, dated July 8, 2008. 

(ii) Reserved. 

(6) The following service information was 

approved for IBR on August 28, 2007 (72 FR 

40222, July 24, 2007). 

(i) Airbus A318/A319/A320/A321 Fuel 

Airworthiness Limitations, Document 

95A.1931/05, Issue 1, dated December 19, 

2005. 

(ii) Reserved. 

(7) 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. 

(8) 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. 

(9) 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/ibr-locations.html. 

Issued in Renton, Washington, on 

September 28, 2016. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–24078 Filed 10–19–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–6538; Directorate 

Identifier 2015–NM–031–AD; Amendment 

39–18668; AD 2016–20–02] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–300, 

–400, and –500 series airplanes. This 

AD was prompted by an evaluation by 

the design approval holder (DAH) 

indicating that the aft pressure bulkhead 

is subject to widespread fatigue damage 

(WFD). This AD requires repetitive 

inspections of the aft pressure bulkhead 

web for any cracking, incorrectly drilled 

fastener holes, and elongated fastener 

holes; and related investigative and 

corrective actions, if necessary. We are 

issuing this AD to detect and correct 

fatigue cracking of the aft pressure 

bulkhead web at the ‘‘Y’’-chord, which 

could result in reduced structural 


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72512 Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations 

integrity of the airplane and rapid 

decompression of the fuselage. 

DATES: This AD is effective November 

25, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 25, 2016. 

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– 

6538. 

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– 

6538; 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: 

Payman Soltani, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

CA 90712–4137; telephone: 562–627– 

5313; fax: 562–627–5210; email: 

payman.soltani@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes. The 

NPRM published in the Federal 

Register on November 30, 2015 (80 FR 

74731) (‘‘the NPRM’’). The NPRM was 

prompted by an evaluation by the DAH 

indicating that the aft pressure bulkhead 

is subject to WFD. The NPRM proposed 

to require repetitive inspections of the 

aft pressure bulkhead web for any 

cracking, incorrectly drilled fastener 

holes, and elongated fastener holes, and 

related investigative and corrective 

actions, if necessary. We are issuing this 

AD to detect and correct fatigue 

cracking of the aft pressure bulkhead 

web at the ‘‘Y’’-chord, which could 

result in reduced structural integrity of 

the airplane and rapid decompression of 

the fuselage. 

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 

the installation of winglets per 

supplemental type certificate (STC) 

ST01219SE does not affect the 

accomplishment of the manufacturer’s 

service instructions. 

We agree with the commenter. We 

have redesignated paragraph (c) of the 

NPRM as paragraph (c)(1) in this final 

rule and added a new paragraph (c)(2) 

to state that STC ST01219SE does not 

affect the mitigating action or 

accomplishment of 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 39.71. 

Request To Clarify the Proposed 

Requirements of the NPRM 

Mr. Cas Lausberg stated that the 

subject of the NPRM is addressed in AD 

99–08–23, Amendment 39–11132 (64 

FR 19879, April 23, 1999) (‘‘AD 99–08– 

23’’), which was superseded by AD 

2012–18–13 R1, Amendment 39–17429 

(78 FR 27020, May 9, 2013) (‘‘AD 2012– 

18–13 R1’’). The commenter questioned 

the need for the new NPRM. 

We agree to provide clarification. As 

stated in the ‘‘Discussion’’ section of the 

NPRM, this final rule is being issued as 

part of the overall joint effort by Boeing 

and the FAA to satisfy requirements of 

the FAA’s WFD final rule (75 FR 69746, 

November 15, 2010), which became 

effective on January 14, 2011. The 

inspections required by AD 99–08–23 

and AD 2012–18–13 R1 do not address 

WFD concerns. However, Boeing Alert 

Service Bulletin 737–53A1214, Revision 

5, dated January 30, 2015, addresses 

WFD with new inspection requirements, 

which incorporate a compliance time 

(threshold) corresponding to the WFD 

inspection start point (ISP) and shorter 

repetitive intervals where indicated. 

These requirements are included in this 

AD. We have not changed this AD in 

this regard. 

Request To Revise the Term ‘‘Global 

Fatigue Damage’’ 

Boeing requested that the term ‘‘global 

fatigue damage’’ be changed to 

‘‘widespread fatigue damage’’ in the 

NPRM. Boeing stated that this is the first 

time it has seen the term ‘‘global’’ used 

to describe WFD. Boeing commented 

that it is better not to introduce a new 

term. 

We agree with the commenter. 

Although the ‘‘Discussion’’ section of 

the proposed rule is not carried over 

into the final rule, we agree that the 

term ‘‘global fatigue damage’’ should not 

be introduced as a new term. We have 

not changed this AD in this regard. 

Request To Correct Reference to Group 

1 LOV (Limit of Validity) 

Boeing requested that we change the 

wording in the ‘‘Differences Between 

This Proposed AD and the Service 

Information’’ paragraph of the NPRM, 

which referred to WFD-based 

inspections specified in certain tables of 

Boeing Alert Service Bulletin 737– 

53A1214, Revision 5, dated January 30, 

2015. The NPRM stated that the WFDbased inspections would affect only 

Group 2 airplanes because Group 1 

airplanes will reach their LOV before 

the compliance times specified ‘‘in 

tables 9, 10, and 11’’ of Boeing Alert 

Service Bulletin 737–53A1214, Revision 

5, dated January 30, 2015. 

Boeing stated that the inspections 

listed in tables 9, 10, and 11 of Boeing 

Alert Service Bulletin 737–53A1214, 

Revision 5, dated January 30, 2015, also 

include non-WFD inspections that are 

required prior to the ISP threshold of 

76,000 cycles. Boeing stated that, 

therefore, it is not true to say that Group 

1 airplanes will reach their limit of 

validity before the compliance times 

specified in tables 9, 10 and 11. 

We partially agree with the 

commenter. Although the ‘‘Differences 

Between This Proposed AD and the 

Service Information’’ paragraph of the 

proposed rule is not carried over into 

the final rule, we agree to provide 

clarification. 

Since AD 2012–18–13 R1 was issued, 

Boeing issued Alert Service Bulletin 

737–53A1214, Revision 5, dated January 

30, 2015. Affected airplanes are now 

divided into two groups: Group 1, line 

numbers 1 through 2565 inclusive; and 

Group 2, line numbers 2566 through 


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3132 inclusive. Boeing’s evaluation 

determined that inspections to address 

WFD concerns are required for the aft 

pressure bulkhead web at the ‘‘Y’’ chord 

at an ISP of 76,000 total flight cycles. 

Since Group 1 airplanes will reach their 

LOV of 75,000 total flight cycles (34,000 

total flight cycles for line numbers 1 

through 291 inclusive), which is prior to 

this ISP, no WFD inspections are 

provided for those airplanes. For Group 

2 airplanes, which have an LOV of 

85,000 total flight cycles, new tables 9, 

10, and 11 of Boeing Alert Service 

Bulletin 737–53A1214, Revision 5, 

dated January 30, 2015, include 

inspections to address WFD. We have 

not changed this AD in this regard. 

Request To Clarify the Applicability 

Boeing requested that we clarify the 

applicability of the proposed AD. 

Boeing stated that Model 737–100, –200, 

and –200C airplanes should be removed 

from the ‘‘Applicability’’ paragraph. 

Boeing stated that the Group 2 airplanes 

only include Model 737–300, –400, and 

–500 airplanes. 

We agree with the commenter’s 

request for the reasons stated above. We 

have revised the applicability in 

paragraph (c) of this AD to remove 

Model 737–100, –200, and –200C series 

airplanes and revised the SUMMARY

section to specify certain Model 737– 

300, –400, and –500 series airplanes. 

Request To Clarify Airplanes Affected 

by Terminating Action Provisions 

Boeing requested that we change the 

wording for the terminating action in 

paragraph (j) of the proposed AD. 

Boeing stated that the paragraph should 

specify that the terminating action 

applies only to Group 2 airplanes. 

Boeing stated that specifying Group 2 

airplanes clearly states the intent of the 

terminating action. 

We agree with the commenter’s 

request for the reasons stated above. We 

have expanded the structure of 

paragraph (j) of this AD accordingly. In 

addition, we have clarified that the 

terminating action does not apply to 

stringer S–5L to S–7L and stringer S–5R 

to S–9R, as specified in AD 2012–18–13 

R1 and Boeing Alert Service Bulletin 

737–53A1214, Revision 5, dated January 

30, 2015. 

Request To Revise the Inspections for 

Group 2 Airplanes 

All Nippon Airways (ANA) requested 

that we revise the inspection 

requirements in the proposed AD for 

Group 2 airplanes. ANA requested that 

we either mandate the inspections in 

tables 10 and 11 of Boeing Alert Service 

Bulletin 737–53A1214, Revision 5, 

dated January 30, 2015, for only Group 

2 airplanes with 76,000 flight cycles and 

more, or create a new NPRM to 

supersede AD 2012–18–13 R1 to 

mandate all inspection requirements 

using Boeing Alert Service Bulletin 

737–53A1214, Revision 5, dated January 

30, 2015. ANA stated that if a new 

proposed rule is created, it requests that 

credit be given for any previously 

approved AMOCs to AD 2012–18–13 

R1, to reduce additional burden for 

operators and the FAA. 

We agree with the commenter’s 

request for the reasons stated by the 

commenter. The intent of this final rule 

is to address the WFD concerns in 

accordance with the FAA’s WFD final 

rule (75 FR 69746, November 15, 2010). 

We have revised paragraphs (g), (h), and 

(l) of this AD accordingly. 

Additional Changes to This AD 

In paragraphs (g) and (h) of this AD, 

we have clarified the compliance times 

by explicitly stating the compliance 

times instead of referring to the 

compliance tables in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 5, 

dated January 30, 2015. 

The actions in paragraph (h) of the 

proposed AD states to do detailed and 

eddy current inspections of the aft 

pressure bulkhead web from the forward 

or aft side of the bulkhead for any 

cracking, incorrectly drilled fastener 

hole, and elongated fastener hole. In this 

AD, we have clarified the actions by 

providing the operators the option of 

doing detailed and LFEC inspections 

from the aft side of the aft pressure 

bulkhead, or doing a detailed and HFEC 

inspections from the forward side of the 

aft pressure bulkhead, for any cracking, 

incorrectly drilled fastener hole, and 

elongated fastener hole. 

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 737–53A1214, Revision 5, 

dated January 30, 2015. The service 

information describes procedures for, 

among other actions, repetitive 

inspections of the aft pressure bulkhead 

web for any cracking, incorrectly drilled 

fastener holes, and elongated fastener 

holes; and related investigative and 

corrective actions. 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 122 

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 of the web 

at the ‘‘Y’’-chord.

Up to 60 work-hours × $85 per hour = Up to 

$5,100 per inspection cycle.

$0 Up to $5,100 per inspection cycle.Up to $622,200 per inspection cycle. 

We have received no definitive data 

that will 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: 


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‘‘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 

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 adding 

the following new airworthiness 

directive (AD): 

2016–20–02 The Boeing Company: 

Amendment 39–18668; Docket No. 

FAA–2015–6538; Directorate Identifier 

2015–NM–031–AD. 

(a) Effective Date 

This AD is effective November 25, 2016. 

(b) Affected ADs 

This AD affects AD 2012–18–13 R1, 

Amendment 39–17429 (78 FR 27020, May 9, 

2013) (‘‘AD 2012–18–13 R1’’). 

(c) Applicability 

(1) This AD applies to The Boeing 

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

series airplanes, certificated in any category, 

identified as Group 2 in Boeing Alert Service 

Bulletin 737–53A1214, Revision 5, dated 

January 30, 2015. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/EBD1CEC7B301293E8625

7CB30045557A?

OpenDocument&Highlight=st01219s) 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 indicating that 

the aft pressure bulkhead is subject to 

widespread fatigue damage. We are issuing 

this AD to detect and correct fatigue cracking 

of the aft pressure bulkhead web at the ‘‘Y’’- 

chord, which could result in reduced 

structural integrity of the airplane and rapid 

decompression of the fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections of the Aft Pressure 

Bulkhead Web at the ‘‘Y’’-Chord Upper 

Bulkhead 

Within 76,000 total flight cycles, or within 

4,500 flight cycles since the most recent low 

frequency eddy current (LFEC) inspection 

accomplished in accordance with AD 2012– 

18–13 R1, or within 9,500 flight cycles since 

the most recent high frequency eddy current 

(HFEC) inspection accomplished in 

accordance with AD 2012–18–13 R1, 

whichever occurs latest: Do detailed and 

LFEC inspections from the aft side of the aft 

pressure bulkhead web, or do detailed and 

HFEC inspections from the forward side of 

the aft pressure bulkhead web, for any 

cracking, incorrectly drilled fastener hole, 

and elongated fastener hole, and do all 

applicable related investigative and 

corrective actions, in accordance with Part I 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1214, 

Revision 5, dated January 30, 2015, except as 

required by paragraph (i) of this AD. Do all 

related investigative and corrective actions 

before further flight. If any cracking, 

incorrectly drilled fastener hole, or elongated 

fastener hole is found, before further flight, 

repair the aft pressure bulkhead web using a 

method approved in accordance with the 

procedures specified in paragraph (l) of this 

AD. Thereafter, repeat the inspections at the 

applicable times specified in table 10 of 

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

Service Bulletin 737–53A1214, Revision 5, 

dated January 30, 2015. 

(h) Repetitive Inspections of the Aft Pressure 

Bulkhead Web at the ‘‘Y’’-Chord Below S–15 

Within 76,000 total flight cycles, or within 

4,500 flight cycles since the most recent 

LFEC inspection accomplished in accordance 

with AD 2012–18–13 R1, or within 9,500 

flight cycles since the most recent HFEC 

inspection accomplished in accordance with 

AD 2012–18–13 R1, whichever occurs latest: 

Do detailed and LFEC inspections from the 

aft side of the aft pressure bulkhead, or do 

detailed and HFEC inspections from the 

forward side of the aft pressure bulkhead, for 

any cracking, incorrectly drilled fastener 

hole, and elongated fastener hole, and do all 

applicable corrective actions, in accordance 

with Part III of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1214, Revision 5, dated January 30, 

2015, except as required by paragraph (i) of 

this AD. Do all corrective actions before 

further flight. If any cracking, incorrectly 

drilled fastener hole, or elongated fastener 

hole is found, before further flight, repair the 

aft pressure bulkhead web using a method 

approved in accordance with the procedures 

specified in paragraph (l) of this AD. 

Thereafter, repeat the inspections at the 

applicable times specified in table 11 of 

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

Alert Service Bulletin 737–53A1214, 

Revision 5, dated January 30, 2015. 

(i) Exception to the Service Information 

Where Boeing Alert Service Bulletin 737– 

53A1214, Revision 5, dated January 30, 2015, 

specifies to contact Boeing for repair 

instructions: Before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (l) of 

this AD. 

(j) Terminating Action for Other Rulemaking 

(1) For Group 2 airplanes specified in 

Boeing Alert Service Bulletin 737–53A1214, 

Revision 5, dated January 30, 2015: 

Accomplishing the actions required by 

paragraph (g) of this AD terminates the 

inspections required by paragraph (k) of AD 

2012–18–13 R1, except for stringer S–5L to 

S–7L and stringer S–5R to S–9R. 

(2) For Group 2 airplanes specified in 

Boeing Alert Service Bulletin 737–53A1214, 

Revision 5, dated January 30, 2015: 

Accomplishing the actions required by 

paragraph (h) of this AD terminates the 

inspections required by paragraph (l) of AD 

2012–18–13 R1. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

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

this AD, if the actions were performed before 

the effective date of this AD using Boeing 

Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011. 


asabaliauskas on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Rules and Regulations 72515 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 (m)(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 Organization 

Designation Authorization (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 previously for AD 

2012–18–13 R1, Amendment 39–17429 (78 

FR 27020, May 9, 2013), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Payman Soltani, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles ACO, 3960 Paramount Boulevard, 

Lakewood CA 90712–4137; telephone: 562– 

627–5313; fax: 562–627–5210; email: 

payman.soltani@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(n) 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– 

53A1214, Revision 5, dated January 30, 2015. 

(ii) Reserved. 

(3) 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. 

(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 

September 16, 2016. 

Thomas Groves, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–23078 Filed 10–19–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–0465; Directorate 

Identifier 2015–NM–096–AD; Amendment 

39–18679; AD 2016–20–13] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A330–200 and –300 series 

airplanes; and Model A340–200 and 

–300 series airplanes. This AD was 

prompted by a determination that the 

compliance times for certain post-repair 

inspections and certain allowable 

damage limits (ADLs) must be reduced 

in order to address fatigue. This AD 

requires identifying any repairs and 

ADLs used to assess or control any 

structural damage on certain structural 

areas, and corrective action if necessary. 

We are issuing this AD to prevent 

fatigue damage on primary structure and 

structural repairs, which could result in 

reduced structural integrity of the 

airplane. 

DATES: This AD is effective November 

25, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 25, 2016. 

ADDRESSES: For service information 

identified in this final rule, 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. 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–2016–0465. 

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–2016– 

0465; 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 street address for 

the Docket Office (telephone: 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone: 425–227–1138; 

fax: 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Airbus Model A330– 

200 and –300 series airplanes; and 

Model A340–200 and –300 series 

airplanes. The NPRM published in the 

Federal Register on February 18, 2016 

(81 FR 8160) (‘‘the NPRM’’). The NPRM 

was prompted by a determination that 

the compliance times for certain postrepair inspections and certain ADLs 

must be reduced in order to address 

fatigue. The NPRM proposed to require 

identifying any repairs and ADLs used 

to assess or control any structural 

damage on certain structural areas, and 

corrective action if necessary. We are 

issuing this AD to prevent fatigue 

damage on primary structure and 

structural repairs, which could result in 

reduced structural integrity of the 

airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2015– 

0101R1, dated June 12, 2015 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 


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