This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

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new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

39541 

Vol. 81, No. 117 

Friday, June 17, 2016 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–3988; Directorate 

Identifier 2015–NM–130–AD; Amendment 

39–18546; AD 2016–11–19] 

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, –200 

Freighter, and –300 series airplanes; and 

all Airbus Model A340–200, –300, –500, 

and –600 series airplanes. This AD was 

prompted by reports of chafing of the 

feeder cable at the pylon-wing junction 

due to vibration; one report revealed 

that the cable loom plastic support 

bracket of the G-route was broken due 

to vibration; and another report revealed 

wire chafing due to clamp damage. This 

AD requires modifying the cable loom 

support bracket of the G-route of the 

inboard pylons at the pylon-wing 

junction. We are issuing this AD to 

prevent chafing of the wiring in the 

pylon-wing area, which could result in 

an electrical short circuit near a 

flammable fluid vapor zone, and 

consequent fire or fuel tank explosion. 

DATES: This AD is effective July 22, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 22, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus SAS, Airworthiness Office— 

EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone 

+33 5 61 93 36 96; fax +33 5 61 93 45 

80; email airworthiness.A330-A340@

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–2016–3988. 

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– 

3988; 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, –200 Freighter, and –300 series 

airplanes; and all Airbus Model A340– 

200, –300, –500, and –600 series 

airplanes. The NPRM published in the 

Federal Register on March 1, 2016 (81 

FR 10549) (‘‘the NPRM’’). The NPRM 

was prompted by reports of chafing of 

the feeder cable at the pylon-wing 

junction due to vibration; one report 

revealed that the cable loom plastic 

support bracket of the G-route was 

broken due to vibration; and another 

report revealed wire chafing due to 

clamp damage. The NPRM proposed to 

require modifying the cable loom 

support bracket of the G-route of the 

inboard pylons at the pylon-wing 

junction. We are issuing this AD to 

prevent chafing of the wiring in the 

pylon-wing area, which could result in 

an electrical short circuit near a 

flammable fluid vapor zone, and 

consequent fire or fuel tank explosion. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2015–0142, dated July 17, 

2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Airbus 

Model A330–200, –200 Freighter, and 

–300 series airplanes; and all Airbus 

Model A340–200, –300, –500, and –600 

series airplanes. The MCAI states: 

Two events have been reported of feeder 

cable chafing at the pylon-wing junction on 

A330 aeroplanes. Inspection of the affected 

area for the first event revealed that the 

bracket supporting the cables G-route, made 

in plastic, was broken. The second event was 

due to clamp damage. Failure of support 

bracket and/or damage of clamp led to the 

feeder cables gradually chafing away at the 

cut-out edge by vibration. Due to design 

similarity, A340 aeroplanes are also affected 

by this issue. 

This condition, if not corrected, could 

create a short circuit, in combination with 

fuel vapour on [the] ground, possibly 

resulting in a fire or explosion. 

To address this unsafe condition, Airbus 

developed modifications to be embodied in 

service through Airbus Service Bulletin (SB) 

A330–92–3132, SB A340–92–4100 or SB 

A340–92–5066, as applicable to aeroplane 

type and model. 

For the reasons described above, this 

[EASA] AD requires the embodiment of these 

modifications [of the cable loom support 

bracket of the G-route of the inboard pylons] 

at the pylon/wing junction in [left-hand] LH 

and [right-hand] RH wings. 

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–2016– 

3988. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 


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39542 Federal Register / Vol. 81, No. 117 / Friday, June 17, 2016 / Rules and Regulations 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, except for 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. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following Airbus 

service information: 

• Service Bulletin A330–92–3132, 

Revision 01, dated May 21, 2015. 

• Service Bulletin A340–92–4100, 

Revision 01, dated May 21, 2015. 

• Service Bulletin A340–92–5066, 

dated June 25, 2014. 

This service information describes 

procedures for modifying the cable loom 

support bracket of the G-route of the 

inboard pylons at the pylon-wing 

junction. 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 90 

airplanes of U.S. registry. 

We also estimate that it takes about 8 

work-hours per product to comply with 

the modification requirements of this 

AD. Required parts will cost about $900 

per product. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost for the 

inspection specified in this AD on U.S. 

operators to be $142,200, or $1,580 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): 

2016–11–19 Airbus: Amendment 39–18546; 

Docket No. FAA–2016–3988; Directorate 

Identifier 2015–NM–130–AD. 

(a) Effective Date 

This AD is effective July 22, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

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

certificated in any category, all manufacturer 

serial numbers. 

(1) Airbus Model A330–201, –202, –203, 

–223, –223F, –243, –243F, –301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes; except airplanes on which Airbus 

Modification 203672 has been embodied in 

production. 

(2) Airbus Model A340–211, –212, –213, 

–311, –312, –313, –541, and –642 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/Furnishings. 

(e) Reason 

This AD was prompted by reports of 

chafing of the feeder cable at the pylon-wing 

junction due to vibration; one report revealed 

that the cable loom plastic support bracket of 

the G-route was broken due to vibration; and 

another report revealed wire chafing due to 

clamp damage. We are issuing this AD to 

prevent chafing of the wiring in the pylonwing area, which could result in an electrical 

short circuit near a flammable fluid vapor 

zone, and consequent fire or fuel tank 

explosion. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification of the Feeder Cable 

Within 18 months after the effective date 

of this AD: Modify the cable loom support 

bracket of the G-route 7701VB in the lefthand side of the inboard pylon, and the Groute 7702VB in the right-hand side of the 

inboard pylon, located at the pylon-wing 

junction, in accordance with the applicable 

service information specified in paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD. 

(1) Airbus Service Bulletin A330–92–3132, 

Revision 01, dated May 21, 2015. 

(2) Airbus Service Bulletin A340–92–4100, 

Revision 01, dated May 21, 2015. 

(3) Airbus Service Bulletin A340–92–5066, 

dated June 25, 2014. 

(h) Credit for Previous Actions 

This paragraph provides credit for the 

modification required by paragraph (g) of this 

AD, if the modification was performed before 

the effective date of this AD using Airbus 

Service Bulletin A330–92–3132, dated June 

19, 2014; or Airbus Service Bulletin A340– 

92–4100, dated June 19, 2014; as applicable. 

This service information is not incorporated 

by reference in this AD. 

(i) 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 


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Federal Register / Vol. 81, No. 117 / Friday, June 17, 2016 / Rules and Regulations 39543 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

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. 

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. 

(3) Required for Compliance (RC): 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. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0142, dated 

July 17, 2015, 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– 

2016–3988. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (k)(4) and (k)(5) of this AD. 

(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 this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on July 22, 2016. 

(i) Airbus Service Bulletin A330–92–3132, 

Revision 01, dated May 21, 2015. 

(ii) Airbus Service Bulletin A340–92–4100, 

Revision 01, dated May 21, 2015. 

(iii) Airbus Service Bulletin A340–92– 

5066, dated June 25, 2014. 

(4) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(5) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

(6) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

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

Issued in Renton, Washington, on May 26, 

2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–13105 Filed 6–16–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8467; Directorate 

Identifier 2014–NM–107–AD; Amendment 

39–18541; AD 2016–11–14] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Fokker Services B.V. Model F.28 Mark 

1000, 2000, 3000, and 4000 airplanes. 

This AD was prompted by a design 

review that revealed no controlled 

bonding provisions are present on a 

number of critical locations inside the 

fuel tanks or connected to the walls of 

the fuel tanks. This AD requires 

installing additional and improved 

bonding provisions in the fuel tanks and 

revising the airplane maintenance or 

inspection program, as applicable, by 

incorporating fuel airworthiness 

limitation items and critical design 

configuration control limitations 

(CDCCLs). We are issuing this AD to 

prevent an ignition source in the fuel 

tank vapor space, which could result in 

a fuel tank explosion and consequent 

loss of the airplane. 

DATES: This AD is effective July 22, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 22, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Fokker Services B.V., Technical 

Services Dept., P.O. Box 1357, 2130 EL 

Hoofddorp, the Netherlands; telephone 

+31 (0)88–6280–350; fax +31 (0)88– 

6280–111; email 

technicalservices@fokker.com; Internet 

http://www.myfokkerfleet.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– 

8467. 

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– 

8467; 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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1137; 

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 Fokker Services B.V. Model 

F.28 Mark 1000, 2000, 3000, and 4000 

airplanes. The NPRM published in the 

Federal Register on January 20, 2016 

(81 FR 3051) (‘‘the NPRM’’). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0108, dated May 8, 2014 

(referred to after this the Mandatory 

Continuing Airworthiness Information, 


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