44496 Federal Register / Vol. 81, No. 131 / Friday, July 8, 2016 / Rules and Regulations 

(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): 

2016–13–13 Beechcraft Corporation (Type 

Certificate Previously Held by Hawker 

Beechcraft Corporation; Raytheon 

Aircraft Company): Amendment 39– 

18577; Docket No. FAA–2016–0460; 

Directorate Identifier 2015–NM–078–AD. 

(a) Effective Date 

This AD is effective August 12, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Beechcraft Corporation 

(type certificate previously held by Hawker 

Beechcraft Corporation; Raytheon Aircraft 

Company) airplanes, certificated in any 

category, as identified in paragraphs (c)(1) 

and (c)(2) of this AD. 

(1) Model BAe.125 series 1000A and 1000B 

airplanes, serial numbers 258151, 258159, 

and 259004 through 259042 inclusive. 

(2) Model Hawker 1000 airplanes, serial 

numbers 259003 and 259043 through 259052 

inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 78, Engine Exhaust. 

(e) Unsafe Condition 

This AD was prompted by reports of 

inadvertent stowage of the thrust reversers, 

which can result in high forward engine 

thrust even though the throttle is 

commanding reverse thrust. We are issuing 

this AD to prevent inadvertent stowage of the 

thrust reversers, which could cause a runway 

overrun during a rejected takeoff or landing, 

and consequent structural failure and 

possible injury to occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Installation 

Within 600 flight hours or 12 months after 

the effective date of this AD, whichever 

occurs first: Install kits having part numbers 

140–9005 and 140–9006, in accordance with 

the Accomplishment Instructions of 

Beechcraft Service Bulletin 78–4133, dated 

May 2015, except as specified in paragraph 

(h) of this AD. 

(h) Exception to Service Information 

A note in the Accomplishment Instructions 

of Beechcraft Service Bulletin 78–4133, dated 

May 2015, instructs operators to contact 

Beechcraft Corporation if any difficulty is 

encountered in accomplishing the service 

bulletin. However, any deviation from the 

actions required by paragraph (g) of this AD 

must be approved as an alternative method 

of compliance (AMOC) under the provisions 

of paragraph (i)(1) of this AD. 

(i) Alternative Methods of Compliance 

(1) The Manager, Wichita 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 (j) 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. 

(j) Related Information 

For more information about this AD, 

contact Jeffrey Englert, Aerospace Engineer, 

Systems and Propulsion Branch, ACE–116W, 

FAA, Wichita ACO, 1801 Airport Road, 

Room 100, Dwight D. Eisenhower National 

Airport, Wichita, KS 67209; phone: 316–946– 

4167; fax: 316–946–4107; email: 

jeffrey.englert@faa.gov. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Beechcraft Service Bulletin 78–4133, 

dated May 2015. 

(ii) Reserved. 

(3) For Beechcraft service information 

identified in this AD, contact Beechcraft 

Corporation, TMDC, P.O. Box 85, Wichita, 

KS 67201–0085; telephone: 316–676–8238; 

fax: 316–671–2540; email: tmdc@

beechcraft.com; Internet: http://

pubs.beechcraft.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, June 22, 

2016. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–15622 Filed 7–7–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2964; Directorate 

Identifier 2014–NM–206–AD; Amendment 

39–18584; AD 2016–14–03] 

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 A319, A320, and A321 

series airplanes. This AD is intended to 

complete certain mandated programs 

intended to support the airplane 

reaching its limit of validity (LOV) of 

the engineering data that support the 

established structural maintenance 

program. This AD requires reinforcing 

the forward pressure bulkhead at a 

certain stringer on both the left-hand 

and right-hand sides, and doing related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

prevent fatigue cracking of the forward 

pressure bulkhead, which could result 

in reduced structural integrity of the 

airplane. 

DATES: This AD becomes effective 

August 12, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 12, 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 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 131 / Friday, July 8, 2016 / Rules and Regulations 44497 

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–2015– 

2964. 

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– 

2964; 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: 

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 A319, A320, 

and A321 series airplanes. The NPRM 

published in the Federal Register on 

July 30, 2015 (80 FR 45457) (‘‘the 

NPRM’’). The NPRM was intended to 

complete certain mandated programs 

intended to support the airplane 

reaching its LOV of the engineering data 

that support the established structural 

maintenance program. The NPRM 

proposed to require reinforcing the 

forward pressure bulkhead at a certain 

stringer on both the left-hand and righthand sides, and doing related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

prevent fatigue cracking of the forward 

pressure bulkhead, 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 Airworthiness 

Directive 2014–0209, dated September 

19, 2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition on all Model A319, 

A320, and Model A321 series airplanes. 

The MCAI states: 

During the A320 fatigue test campaign for 

Extended Service Goal (ESG), it was 

determined that fatigue damage could 

develop on the forward pressure bulkhead at 

Frame (FR) 35 on left hand (LH) side and 

right hand (RH) side. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To address this potential unsafe condition, 

a reinforcement modification was developed, 

which has been published through Airbus 

Service Bulletin (SB) A320–53–1268 for inservice application to allow aeroplanes to 

operate up to the new ESG limit. 

For the reasons described above, this 

[EASA] AD requires reinforcement of the 

centre fuselage forward pressure bulkhead at 

FR35. 

The forward pressure bulkhead 

reinforcement includes related 

investigative actions of measuring the 

diameters of certain fastener holes, and 

if they are not oversized, doing a 

rotating probe inspection for cracking of 

the fastener holes. 

Required corrective actions include 

cold expanding crack-free holes or 

repairing oversize or cracked holes by 

using a method approved by the FAA, 

EASA, or Airbus’s EASA Design 

Organization Approval (DOA). 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

2964–0002. 

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. 

Request To Reference Revised Service 

Information 

American Airlines requested that we 

reference Revision 03 of Airbus Service 

Bulletin A320–53–1268, dated May 7, 

2015, as the appropriate source of 

service information. 

We agree with American Airlines’ 

request. No additional work is specified 

by this revision for airplanes modified 

by any previous issue. We have revised 

paragraphs (g) and (h) of this AD to refer 

to Airbus Service Bulletin A320–53– 

1268, Revision 03, dated May 7, 2015; 

and revised paragraph (i) of this AD to 

also give credit for previous actions 

accomplished in accordance with 

Airbus Service Bulletin A320–53–1268, 

Revision 02, dated July 15, 2014. 

Request for Applicability Clarification 

United Airlines (UAL) stated that the 

effectivity of Airbus Service Bulletin 

A320–53–1268, Revision 02, dated July 

15, 2014, does not match the NPRM 

applicability. UAL also stated that the 

NPRM applicability does not mention 

pre-modification 153832 airplanes, and 

that Airbus Service Bulletin A320–53– 

1268, Revision 02, dated July 15, 2014, 

is classified as Airbus Modification 

153832. 

UAL stated that several alternative 

methods of compliance (AMOCs) may 

be needed because Airbus will add to 

the effectivity of Airbus Service Bulletin 

A320–53–1268, Revision 02, dated July 

15, 2014, after operators purchase an 

extended design service goal from 

Airbus. 

We agree to clarify the applicability. 

The requirements of this AD apply to all 

airplanes identified in the applicability 

of the AD. If there is any conflict 

between the AD applicability and the 

service information effectivity, then the 

AD takes precedence. The applicability 

of this AD also matches the applicability 

of the corresponding MCAI AD. 

If operators are planning to operate 

the airplane beyond the LOV of 

engineering data approved for the 

original type design, the actions 

specified in this AD must be done in 

order to address the identified unsafe 

condition. We acknowledge that 

AMOCs may be needed to allow the use 

of future revisions of the service 

information. Therefore, we encourage 

operators to coordinate with Airbus for 

effective planning and compliance with 

the AD requirements if they intend to 

operate their fleet beyond its LOV. We 

have not changed this final rule in this 

regard. 

Request for Terminating Action 

Clarification 

UAL questioned why there is no 

terminating action in the proposed AD. 

UAL stated that the reinforcement 

specified in this proposed AD is 

intended to prevent fatigue cracking of 

the forward pressure bulkhead but there 

is no reference to related inspection 

tasks or termination of existing 

Airworthiness Limitation Items (ALIs). 

UAL noted that, for example, ALI 

533186 is applicable for pre-Mod 

153832 (Airbus Service Bulletin A320– 

53–1268) airplanes. UAL stated this will 

cause confusion as to whether or not 

ALI inspections are required if there is 

no terminating action paragraph. 

In regard to UAL’s question on 

terminating action, ALI inspections 


jstallworth on DSK7TPTVN1PROD with RULES
44498 Federal Register / Vol. 81, No. 131 / Friday, July 8, 2016 / Rules and Regulations 

must be accomplished on an airplane to 

be in compliance with the approved 

type design independent of the forward 

pressure bulkhead reinforcement 

required by this AD. Accomplishing the 

reinforcement does not preclude the 

need for ALI inspections. 

However, when the effectivity of an 

ALI inspection identifies premodification airplanes, then it is not 

applicable to airplanes in a postmodification configuration. Thus, ALI 

inspections that are identified as preMod 153832 (Airbus Service Bulletin 

A320–53–1268) do not affect airplanes 

on which the reinforcement specified in 

Airbus Service Bulletin A320–53–1268 

has been done. We have not changed 

this AD in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM 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 

Airbus has issued Service Bulletin 

A320–53–1268, Revision 03, dated May 

7, 2015. The service information 

describes procedures for reinforcing the 

forward pressure bulkhead at frame 35, 

stringer 30, on both the left-hand and 

right-hand sides; and for doing 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 of 

this AD. 

Costs of Compliance 

We estimate that this AD affects 48 

airplanes of U.S. registry. 

We also estimate that it will take 

about 21 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $85,680, or $1,785 per 

product. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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. 

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): 

2016–14–03 Airbus: Amendment 39–18584. 

Docket No. FAA–2015–2964; Directorate 

Identifier 2014–NM–206–AD. 

(a) Effective Date 

This AD becomes effective August 12, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes, 

certificated in any category, identified in 

paragraphs (c)(1), (c)(2), and (c)(3) of this AD, 

all manufacturer serial numbers. 

(1) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes. 

(2) Airbus Model A320–211, –212, –214, 

–231, –232, and –233 airplanes. 

(3) Airbus Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD is intended to complete certain 

mandated programs intended to support the 

airplane reaching its limit of validity (LOV) 

of the engineering data that support the 

established structural maintenance program. 

We are issuing this AD to prevent fatigue 

cracking of the forward pressure bulkhead, 

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) Reinforcement, Related Investigative 

Actions, and Corrective Actions 

Before the accumulation of 48,000 total 

flight cycles or 96,000 total flight hours, 

whichever occurs first: Reinforce the forward 

pressure bulkhead at frame 35, stringer 30, on 

both the left-hand and right-hand sides; and 

do all applicable related investigative and 

corrective actions; in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1268, Revision 03, 

dated May 7, 2015, except as provided by 

paragraph (h) of this AD. Do all applicable 

related investigative and corrective actions 

before further flight. 

(h) Exception to Service Information 

Specifications 

Although Airbus Service Bulletin A320– 

53–1268, Revision 03, dated May 7, 2015, 

specifies to contact Airbus for repair 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 131 / Friday, July 8, 2016 / Rules and Regulations 44499 

instructions, and specifies that action as 

‘‘RC’’ (Required for Compliance), this AD 

requires repair before further flight 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). 

(i) Credit for Previous Actions 

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 any of the Airbus 

service information specified in paragraphs 

(i)(1) through (i)(3) of this AD. This service 

information is not incorporated by reference 

in this AD. 

(1) Airbus Service Bulletin A320–53–1268, 

dated January 8, 2013, which is not 

incorporated by reference in this AD. 

(2) Airbus Service Bulletin A320–53–1268, 

Revision 01, dated July 23, 2013, which is 

not incorporated by reference in this AD. 

(3) Airbus Service Bulletin A320–53–1268, 

Revision 02, dated July 15, 2014, which is 

not incorporated by reference in this AD. 

(j) 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 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (h) of this AD, if 

any service information contains procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

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 procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2014–0209, dated September 19, 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–2015–2964. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A320–53–1268, 

Revision 03, dated May 7, 2015. 

(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 June 23, 

2016. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–15909 Filed 7–7–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–5808; Directorate 

Identifier 2015–NM–111–AD; Amendment 

39–18585; AD 2016–14–04] 

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 water leakage from the 

potable water system due to improperly 

installed waterline couplings, and water 

leaking into the electronics equipment 

(EE) bays from above the floor in the 

main cabin, resulting in water on the 

equipment in the EE bays. This AD 

requires replacing the potable waterline 

couplings above the forward and aft EE 

bays with new, improved couplings. 

This AD also requires sealing the main 

cabin floor areas above the aft EE bay, 

installing drip shields and foam blocks, 

and rerouting the wire bundles near the 

drip shields above the equipment in the 

aft EE bay. We are issuing this AD to 

prevent a water leak from an improperly 

installed potable water system coupling, 

or main cabin water source, which 

could cause the equipment in the EE 

bays to become wet, resulting in an 

electrical short and potential loss of 

system functions essential for safe flight. 

DATES: This AD is effective August 12, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 12, 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– 

5808. 


jstallworth on DSK7TPTVN1PROD with RULES