68434 Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations 

specifies to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta 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 (k) of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(k) Related Information 

For more information about this AD, Carl 

Gray, Aerospace Engineer, Airframe Branch, 

ACE–117A, FAA, Atlanta ACO, 1701 

Columbia Avenue, College Park, GA 30337; 

phone: 404–474–5554; fax: 404–474–5605; 

email: carl.w.gray@faa.gov. 

(l) 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) Lockheed Martin Electra Service 

Bulletin 88/SB–722, dated April 30, 2014. 

(ii) Reserved. 

(3) For Lockheed service information 

identified in this AD, contact Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company, Airworthiness Office, 

Dept. 6A0M, Zone 0252, Column P–58, 86 S. 

Cobb Drive, Marietta, GA 30063; phone: 770– 

494–5444; fax: 770–494–5445; email: 

ams.portal@lmco.com; Internet http://

www.lockheedmartin.com/ams/tools/

TechPubs.html. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on October 

22, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–27919 Filed 11–4–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0244; Directorate 

Identifier 2014–NM–127–AD; Amendment 

39–18313; AD 2015–22–08] 

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 all 

Airbus Model A318, A319, and A320 

series airplanes. This AD was prompted 

by a cracked upper cardan in the main 

landing gear (MLG). This AD requires 

revising the maintenance or inspection 

program, as applicable, to reduce the 

life limits for the MLG upper cardan for 

certain installations. We are issuing this 

AD to prevent failure of the upper 

cardan in the MLG, which could result 

in MLG collapse and subsequent 

damage to the airplane and injury to 

occupants. 

DATES: This AD becomes effective 

December 10, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 10, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-0244; or in 

person at the 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. 

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.airwortheas@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–2015–0244. 

FOR FURTHER INFORMATION CONTACT: 

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. 

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 all Airbus Model A318, A319, 

and A320 series airplanes. The NPRM 

published in the Federal Register on 

March 5, 2015 (80 FR 11964). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0141, dated June 4, 2014 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for all Airbus Model A318, 

A319, and A320 series airplanes. The 

MCAI states: 

During an A320–200 77T main landing 

gear (MLG) fatigue test by Messier BugattiDowty (MBD), an upper cardan was found 

with a crack, emanating from the grease hole/ 

main lug intersection. The affected upper 

cardan, Part Number (P/N) 201163620, is 

listed in the applicable Airworthiness 

Limitations Section (ALS) Part 1 with a 

demonstrated fatigue life of 60,000 landings. 

This condition, if not corrected, could lead 

to MLG upper cardan failure, possibly 

resulting in MLG collapse and subsequent 

damage to the aeroplane and injury to 

occupants. 

Prompted by these findings and further to 

analysis, it has been decided to reduce the 

life limit for certain installations of the P/N 

201163620 MLG upper cardan. 

For the reasons described above, this AD 

requires implementation of the new life 

limits, as applicable, and replacement of any 

affected MLG upper cardan units that have 

already exceeded the reduced limit. 

The reduced life limits for the affected 

MLG upper cardan are expected to be 

incorporated in a next revision of the Airbus 

A318/A319/A320/A321 ALS Part 1. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-0244- 

0003. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (80 FR 11964, 

March 5, 2015) and the FAA’s response 

to each comment. 

Request To Extend the Compliance 

Time 

Delta Airlines (DAL) requested that 

paragraph (g) of the proposed AD (80 FR 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations 68435 

11964, March 5, 2015) be revised so the 

initial compliance time for replacing the 

MLG upper cardan is extended and 

corresponds to that of European 

Aviation Safety Agency (EASA) AD 

2014–0141, dated June 4, 2014. EASA 

AD 2014–0141 specifies an initial 

compliance time of ‘‘within 3 months’’ 

after the effective date of that EASA AD 

and the proposed AD specified an initial 

compliance time of prior to the 

applicable life limit specified in 

paragraphs (g)(1) through (g)(5), or 

within 30 days after the effective date of 

the AD, whichever occurs later. 

We agree with the commenter’s 

request. In consideration of the average 

utilization rate of affected U.S. 

operators, the practical aspects of an 

orderly modification of the U.S. fleet 

during regular maintenance periods, 

and the availability of required 

modification parts, we have determined 

that a 3 month initial compliance time 

is appropriate for replacing the MLG 

upper cardan. We have changed 

paragraph (g) of this AD accordingly. 

Request To Reference Next Higher Part 

Number Assembly 

Lufthansa Technik requested that the 

part number for the next higher 

assembly of MLG cardan part number 

(P/N) 201163620 be referenced in the 

NPRM (80 FR 11964, March 5, 2015). 

The commenter stated that the NPRM 

and corresponding EASA AD 2014– 

0141, dated June 4, 2014, reference P/N 

201163620, but that part number is not 

identified in the aircraft illustrated parts 

catalog (AIPC). The commenter is 

concerned that if operators only look in 

the AIPC to see if P/N 201163620 is 

identified, and it is not there, they may 

falsely think that their airplanes would 

not be affected by the NPRM. 

We do not agree with the commenter’s 

request. Although MLG cardan P/N 

201163620 is not included in the AIPC, 

it is identified in Airbus A318/A319/

A320/A321 ALS Part 1—Safe Life 

Airworthiness Limitation Items, which 

is part of the approved type design for 

these airplanes. Therefore, we have not 

changed this AD in this regard. 

Clarification of Parts Installation 

Limitation 

In paragraph (j) of the proposed AD 

(NPRM (80 FR 11964, March 5, 2015), 

we referred to applicable life limits in 

paragraphs (g)(1) through (g)(5) of the 

proposed AD. For airplanes other than 

those identified paragraphs (g)(1) 

through (g)(5) of the proposed AD, the 

life limit is in Airbus A318/A319/A320/ 

A321 ALS Part 1—Safe Life 

Airworthiness Limitation, Revision 02, 

dated May 13, 2011, as specified in 

paragraph (h)(5) of this AD. In addition, 

if a part is transferred between 

airplanes, operators must adjust the life 

limit using the method specified in 

Airbus A318/A319/A320/A321 ALS 

Part 1—Safe Life Airworthiness 

Limitation, Revision 02, dated May 13, 

2011, as specified in paragraph (h)(3) of 

this AD. We have clarified paragraph (j) 

of this AD by also referring to 

paragraphs (h)(3) and (h)(5) of this AD. 

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 (80 FR 

11964, March 5, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 11964, 

March 5, 2015). 

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 

Airbus has issued A318/A319/A320/

A321 ALS Part 1—Safe Life 

Airworthiness Limitation Items, 

Revision 02, dated May 13, 2011. This 

document provides revised instructions 

and life limits for airworthiness 

limitations items. 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 of this AD. 

Costs of Compliance 

We estimate that this AD affects 851 

airplanes of U.S. registry. 

We also estimate that it will take 

about 1 work-hour per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

about $0 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $72,335, or $85 

per product. 

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 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 the 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-0244; 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 Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

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: 


jstallworth on DSK7TPTVN1PROD with RULES
68436 Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations 

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): 

2015–22–08 Airbus: Amendment 39–18313. 

Docket No. FAA–2015–0244; Directorate 

Identifier 2014–NM–127–AD. 

(a) Effective Date 

This AD becomes effective December 10, 

2015. 

(b) Affected ADs 

For airplanes with configurations specified 

in paragraphs (g)(1) through (g)(5) of this AD: 

Paragraph (g) of this AD terminates the life 

limit specified in paragraph (n)(1) of AD 

2014–23–15, Amendment 39–18031 (80 FR 

3871, January 26, 2015), for airplanes having 

a main landing gear (MLG) upper cardan part 

number (P/N) 201163620. 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1), (c)(2), and 

(c)(3) of this AD, certificated in any category, 

all manufacturer serial numbers. 

(1) Model A318–111, –112, –121, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model A320–211, –212, –214, –231, 

–232, and –233 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by a cracked upper 

cardan in the main landing gear (MLG). We 

are issuing this AD to prevent failure of the 

upper cardan in the MLG, which could result 

in MLG collapse and subsequent damage to 

the airplane and injury to occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revision to Maintenance or Inspection 

Program 

For airplanes having a MLG upper cardan 

part number (P/N) 201163620: Within 30 

days after the effective date of this AD, revise 

the maintenance or inspection program, as 

applicable, to incorporate the applicable life 

limits for the MLG upper cardan P/N 

201163620 specified in paragraphs (g)(1) 

through (g)(5) of this AD and the life limit 

clarifications specified in paragraph (h) of 

this AD. The initial compliance time for 

replacing the MLG upper cardan is prior to 

the applicable life limit specified in 

paragraphs (g)(1) through (g)(5) of this AD, or 

within 3 months after the effective date of 

this AD, whichever occurs later. 

Accomplishing this revision terminates the 

life limit required by paragraph (n)(1) of AD 

2014–23–15, Amendment 39–18031 (80 FR 

3871, January 26, 2015), for the MLG upper 

cardan P/N 201163620 for that airplane only. 

(1) For Airbus Model A319 series 

airplanes, pre-Airbus Modification 26644, 

excluding corporate jets post-Airbus 

Modification 28238, 28162, and 28342: The 

life limit is 50,590 total flight cycles. 

(2) For Airbus Model A319 series 

airplanes, post-Airbus Modification 26644, 

excluding corporate jets post-Airbus 

Modification 28238, 28162, and 28342: The 

life limit is 56,480 total flight cycles. 

(3) For Airbus Model A320 series airplanes 

pre-Airbus Modification 26644 having weight 

variant (WV) WV011, WV012, WV016, or 

WV018: The life limit is 50,590 total flight 

cycles. 

(4) For Airbus Model A320 series airplanes 

post-Airbus Modification 26644, having 

WV011, WV012, WV016, or WV018: The life 

limit is 56,480 total flight cycles. 

(5) For Airbus Model A320 series airplanes 

post-Airbus Modification 26644, having 

WV015 or WV017: The life limit is 42,140 

total flight cycles. 

(h) Additional Life Limit Clarifications 

(1) The life limits specified in paragraphs 

(g)(1) through (g)(5) of this AD are total flight 

cycles accumulated by the MLG since first 

installation on an airplane. 

(2) The life limits specified in paragraphs 

(g)(1) through (g)(5) of this AD are applicable 

only for the airplane model, configuration 

and WV specified in those paragraphs. 

(3) If a part is transferred between airplanes 

having a different life limit for the MLG unit, 

adjust the life limit using the method 

specified in Airbus A318/A319/A320/A321 

ALS Part 1—Safe Life Airworthiness 

Limitation Items, Revision 02, dated May 13, 

2011. 

Note 1 to paragraphs (h)(3) and (h)(5) of 

this AD: Airbus A318/A319/A320/A321 ALS 

Part 1—Safe Life Airworthiness Limitation 

Items, Revision 02, dated May 13, 2011, is 

already required by paragraph (n) of AD 

2014–23–15, Amendment 39–18031 (80 FR 

3871, January 26, 2015). 

(4) A MLG unit on which Airbus 

Modification 26644 is installed is also known 

as ‘‘enhanced’’ landing gear and is identified 

as P/N 201582xxx Leg and Dressing Series. 

A MLG unit that does not have Airbus 

Modification 26644 installed is identified as 

P/N 201375xxx Leg and Dressing Series. (The 

xxx designation is a placeholder for 

numbers). 

(5) For airplanes with configurations not 

specified in paragraphs (g)(1) through (g)(5) 

of this AD, the life limit for the MLG unit is 

specified in Airbus A318/A319/A320/A321 

ALS Part 1—Safe Life Airworthiness 

Limitation Items, Revision 02, dated May 13, 

2011. 

(i) No Alternative Actions and Intervals 

After the maintenance or inspection 

program, as applicable, has been revised as 

required by paragraph (g) of this AD, no 

alternative actions (e.g., inspections) or 

intervals may be used unless the actions or 

intervals are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (k)(1) of this AD. 

(j) Parts Installation Limitation 

As of the effective date of this AD, a MLG 

upper cardan having P/N 201163620 may be 

installed on an airplane, provided the part 

life has not exceeded the applicable life limit 

specified in paragraphs (g)(1) through (g)(5) 

of this AD, paragraph (h)(3) of this AD, and 

paragraph (h)(5) of this AD, and is replaced 

with a serviceable part prior to exceeding the 

applicable life limit specified in paragraphs 

(g)(1) through (g)(5) of this AD, paragraph 

(h)(3) of this AD, and paragraph (h)(5) of this 

AD. 

(k) 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. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(l) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0141, dated 

June 4, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

#!documentDetail;D=FAA-2015-0244. 

(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 this AD specifies otherwise. 

(i) Airbus A318/A319/A320/A321 ALS Part 

1—Safe Life Airworthiness Limitation Items, 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations 68437 

Revision 02, dated May 13, 2011. The 

revision level of this document is identified 

on only the title page and in the Record of 

Revisions. The revision date is not identified 

on the title page of this document. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

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

93 44 51; email account.airworth-eas@

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

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on October 

22, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–27925 Filed 11–4–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0649; Directorate 

Identifier 2014–NM–132–AD; Amendment 

39–18314; AD 2015–22–09] 

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 787–8 

airplanes. This AD was prompted by 

reports of missing plugs found prior to 

airplane delivery, during manufacturing 

inspections, at various locations in 

certain stringers of the lower lobe cargo 

compartments. This AD requires drilling 

a hole and installing and bonding plugs 

in certain stringers of the lower lobe 

cargo compartments. We are issuing this 

AD to detect and correct missing or 

misaligned plugs which, in the event of 

a fire, could cause an increased rate of 

loss of Halon in the lower cargo 

compartments, and result in the 

inability to extinguish a fire and 

consequent loss of control of the 

airplane. 

DATES: This AD is effective December 

10, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 10, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

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–2014– 

0649. 

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–2014– 

0649; 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: 

Francis Smith, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6596; fax: 

425–917–6590; email: francis.smith@

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 787–8 airplanes. The NPRM 

published in the Federal Register on 

September 23, 2014 (79 FR 56682). The 

NPRM was prompted by reports of 

missing plugs found prior to airplane 

delivery, during manufacturing 

inspections, at various locations in 

certain stringers of the lower lobe cargo 

compartments. The NPRM proposed to 

require drilling a hole and installing and 

bonding plugs in certain stringers of the 

lower lobe cargo compartments. We are 

issuing this AD to detect and correct 

missing or misaligned plugs which, in 

the event of a fire, could cause an 

increased rate of loss of Halon in the 

lower cargo compartments, and result in 

the inability to extinguish a fire and 

consequent loss of control 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 (79 FR 56682, 

September 23, 2014) and the FAA’s 

response to each comment. 

Supportive Comment 

United Airlines stated that it concurs 

with the NPRM (79 FR 56682, 

September 23, 2014), and agrees that the 

detection and correction of the missing 

or misaligned plugs will maintain a 

higher level of safety. 

Request To Delay Issuance of the NPRM 

(79 FR 56682, September 23, 2014) 

All Nippon Airways (ANA) asked that 

we delay issuance of the NPRM (79 FR 

56682, September 23, 2014) until Boeing 

Alert Service Bulletin B787–81205– 

SB530024–00, Issue 001, dated May 15, 

2014 (referred to as the appropriate 

source of service information for 

accomplishing the specified actions), 

can be revised. ANA noted that the 

service information specifies using a 

stringer plug removal/installation tool, 

having tool number (T/N) 

MIT140Z4372–3; however, this tool 

does not work well for doing the 

actions. ANA provided the following 

reasons to substantiate its request: 

• For the instructions specified in 

Task 1 of this service information, the 

connecting tube on the tool (T/N 

140Z4372–8/–15) interferes with the 

fasteners at the section 41/43 joint; 

therefore, the tool cannot be inserted 

into the stringers. The connecting tube 

needs to be shortened in length and 

trimmed to taper. 

• For the instructions specified in 

Task 3 of the service information, the 

tool (T/N 140Z4372–3) cannot be 

inserted at stringers 30R through 35R, 

adjacent to the cargo door, because it 

won’t bend at the location adjacent to 

the stringer end and frame. 

• For the instructions specified in 

Task 3 of the service information, the 

tool (T/N 140Z4372–3) is inserted into 

the stringer from station (STA) 1593 to 


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