Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules 74039 

cooling mode, calculated in section 

4.1.1.2 of this appendix. 

5.2 Seasonally Adjusted Cooling 

Capacity. Calculate the seasonally 

adjusted cooling capacity for portable 

air conditioners, SACC, expressed in 

Btu/h, according to the following: 

SACC = ACC95 × 0.2 + ACC83 × 0.8 

Where: 

ACC95 and ACC83 = adjusted cooling 

capacity, in Btu/h, calculated in 

section 5.1 of this appendix. 

0.2 = weighting factor for ACC95. 

0.8 = weighting factor for ACC83. 

5.3 Annual Energy Consumption. 

Calculate the annual energy 

consumption in each operating mode, 

AECm, expressed in kilowatt-hours per 

year (kWh/year). The annual hours of 

operation in each mode are estimated as 

follows: 

Operating mode 

Annual 

operating 

hours 

Cooling Mode, Dual-Duct 95 °F 1 750 

Cooling Mode, Dual-Duct 83 °F 1 750 

Operating mode 

Annual 

operating 

hours 

Cooling Mode, Single-Duct ........... 750 

Off-Cycle ....................................... 880 

Inactive or Off ............................... 1,355 

1These operating mode hours are for the 

purposes of calculating annual energy consumption under different ambient conditions 

for dual-duct portable air conditioners, and are 

not a division of the total cooling mode operating hours. The total dual-duct cooling mode 

operating hours are 750 hours. 

AECm = Pm × tm × k 

Where: 

AECm = annual energy consumption in 

each mode, in kWh/year. 

Pm = average power in each mode, in 

watts. 

m represents the operating mode (‘‘95’’ 

and ‘‘83’’ cooling mode at the 95 °F 

and 83 °F dry-bulb outdoor 

conditions, respectively for dualduct portable air conditioners, ‘‘SD’’ 

cooling mode for single-duct 

portable air conditioners, ‘‘oc’’ offcycle, and ‘‘ia’’ inactive or ‘‘om’’ off 

mode). 

t = number of annual operating time in 

each mode, in hours. 

k = 0.001 kWh/Wh conversion factor 

from watt-hours to kilowatt-hours. 

Total annual energy consumption in 

all modes except cooling, is calculated 

according to the following: 

AECT = èmAECm

Where: 

AECT = total annual energy 

consumption attributed to all 

modes except cooling, in kWh/year; 

AECm = total annual energy 

consumption in each mode, in 

kWh/year. 

m represents the operating modes 

included in AECT (‘‘oc’’ off-cycle, 

and ‘‘im’’ inactive or ‘‘om’’ off 

mode). 

5.4 Combined Energy Efficiency 

Ratio. Using the annual operating hours, 

as outlined in section 5.3 of this 

appendix, calculate the combined 

energy efficiency ratio, CEER, expressed 

in Btu/Wh, according to the following: 

Where: 

CEERSD and CEERDD = combined energy 

efficiency ratio for single-duct and 

dual-duct portable air conditioners, 

respectively, in Btu/Wh. 

ACC95 and ACC83 = adjusted cooling 

capacity, tested at the 95 °F and 

83 °F dry-bulb outdoor conditions 

in Table 1 of this appendix, in Btu/ 

h, calculated in section 5.1 of this 

appendix. 

AECSD = annual energy consumption in 

cooling mode for single-duct 

portable air conditioners, in kWh/

year, calculated in section 5.3 of 

this appendix. 

AEC95 and AEC83 = annual energy 

consumption for the two cooling 

mode test conditions in Table 1 of 

this appendix for dual-duct portable 

air conditioners, in kWh/year, 

calculated in section 5.3 of this 

appendix. 

AECT = total annual energy 

consumption attributed to all 

modes except cooling, in kWh/year, 

calculated in section 5.3 of this 

appendix. 

t = number of cooling mode hours per 

year, 750. 

k = 0.001 kWh/Wh conversion factor for 

watt-hours to kilowatt-hours. 

0.2 = weighting factor for the 95 °F drybulb outdoor condition test. 

0.8 = weighting factor for the 83 °F drybulb outdoor condition test. 

[FR Doc. 2015–30057 Filed 11–25–15; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–5810; Directorate 

Identifier 2014–NM–116–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Fokker Services B.V. Model F.28 Mark 

0070 and 0100 airplanes. This proposed 

AD was prompted by a design review 

that revealed that a wiring failure, 

external to the center wing fuel tank, 

could cause a hot short circuit to a 

maximum level sensor wire, and result 


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74040 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules 

in excessive heating of the maximum 

level sensor element. This proposed AD 

would require modifying the wiring of 

the maximum level sensors in the center 

wing fuel tank, performing afterinstallation tests, and corrective action 

if necessary. This proposed AD would 

also require revising the airplane 

maintenance or inspection program to 

incorporate fuel airworthiness 

limitation items and critical design 

configuration control limitations. We 

are proposing this AD to prevent the 

potential of ignition sources inside fuel 

tanks, which, in combination with 

flammable fuel vapors, could result in 

fuel tank explosions and consequent 

loss of the airplane. 

DATES: We must receive comments on 

this proposed AD by January 11, 2016. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, 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. 

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– 

5810; 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 proposed 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. Comments will 

be available in the AD docket shortly 

after receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–5810; Directorate Identifier 

2014–NM–116–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0138, dated May 30, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Fokker 

Services B.V. Model F.28 Mark 0070 

and 0100 airplanes. The MCAI states: 

* * * [T]he FAA published Special 

Federal Aviation Regulation (SFAR) 88, and 

the Joint Aviation Authorities (JAA) 

published Interim Policy INT/POL/25/12. 

The review conducted by Fokker Services 

on the Fokker 70/100 design, in response to 

these regulations, revealed that a wiring 

failure, external to the centre wing fuel tank, 

causing a hot short circuit to a maximum 

(max) level sensor wire may result in 

excessive heating of the max level sensor 

element. 

This condition, if not corrected, could 

create an ignition source in the centre wing 

fuel tank vapour space, possibly resulting in 

a fuel tank explosion and consequent loss of 

the aeroplane. 

EASA issued AD 2012–0240 [http://

ad.easa.europa.eu/blob/easa_ad_2012_

0240.pdf/AD_2012-0240], to address this 

unsafe condition, which required installation 

of three fuses in the wiring of the max level 

sensor(s) in the centre wing fuel tank per 

Fokker Services Service Bulletin (SB) 

SBF100–28–073. After that AD was issued, it 

was found that this technical solution caused 

fuel spills during refueling and, 

consequently, EASA cancelled AD 2012– 

0240. 

More recently, Fokker Services issued 

SBF100–28–078, which cancelled SBF100– 

28–073, to correct the unsafe condition 

without the risk of fuel spills. 

For the reasons described above, this 

[EASA] AD requires removal of one fuse from 

post-SBF100–28–073 aeroplanes, and 

installation of only two fuses on pre-SBF100– 

28–073 aeroplanes and, subsequently, the 

implementation of the associated Critical 

Design Configuration Control Limitation 

(CDCCL) items. 

More information this subject can be found 

in Fokker Services All Operators Message 

AOF100.186#03. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating it in Docket No. FAA– 

2015–5810. 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 

Regulation No. 88 (‘‘SFAR 88,’’ 

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 

requires certain type design (i.e., type 

certificate (TC) and supplemental type 

certificate (STC)) holders to substantiate 

that their fuel tank systems can prevent 

ignition sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 

and to develop design changes and 

maintenance procedures if their designs 

do not meet the new fuel tank safety 

standards. As explained in the preamble 

to the rule, we intended to adopt 

airworthiness directives to mandate any 

changes found necessary to address 

unsafe conditions identified as a result 

of these reviews. 

In evaluating these design reviews, we 

have established four criteria intended 

to define the unsafe conditions 

associated with fuel tank systems that 

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Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules 74041 

require corrective actions. The 

percentage of operating time during 

which fuel tanks are exposed to 

flammable conditions is one of these 

criteria. The other three criteria address 

the failure types under evaluation: 

single failures, combination of failures, 

and unacceptable (failure) experience. 

For all three failure criteria, the 

evaluations included consideration of 

previous actions taken that may mitigate 

the need for further action. 

The Joint Aviation Authorities (JAA) 

has issued a regulation that is similar to 

SFAR 88. (The JAA is an associated 

body of the European Civil Aviation 

Conference (ECAC) representing the 

civil aviation regulatory authorities of a 

number of European States who have 

agreed to co-operate in developing and 

implementing common safety regulatory 

standards and procedures.) Under this 

regulation, the JAA stated that all 

members of the ECAC that hold type 

certificates for transport category 

airplanes are required to conduct a 

design review against explosion risks. 

We have determined that the actions 

identified in this AD are necessary to 

reduce the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss of the airplane. 

Related Service Information Under CFR 

Part 51 

Fokker has issued Service Bulletin 

SBF100–28–078, dated January 23, 

2014. The service information describes 

procedures for modifying the wiring of 

the maximum level sensors in the center 

wing fuel tank, after-installation tests, 

and corrective action if necessary. 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 NPRM. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

affects 15 airplanes of U.S. registry. 

We also estimate that it would take up 

to 9 work-hours per product to modify 

the wiring of the maximum level 

sensors in the center wing fuel tank, as 

specified in this proposed AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about $1,700 

per product. Based on these figures, we 

estimate the cost of this proposed 

modification on U.S. operators to be up 

to $36,975, or up to $2,465 per product. 

We also estimate that it would take 

about 1 work-hour per product to revise 

the maintenance or inspection program 

as specified in this proposed AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this proposed revision on U.S. 

operators to be $1,275, 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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Fokker Services B.V.: Docket No. FAA– 

2015–5810; Directorate Identifier 2014– 

NM–116–AD. 

(a) Comments Due Date 

We must receive comments by January 11, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model F.28 Mark 0070 and 0100 airplanes, 

certificated in any category, equipped with a 

center wing tank. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by a design review 

which revealed that a wiring failure, external 

to the center wing fuel tank, could cause a 

hot short circuit to a maximum level sensor 

wire, and result in excessive heating of the 

maximum level sensor element. We are 

issuing this AD to prevent the potential of 

ignition sources inside fuel tanks, which, in 

combination with flammable fuel vapors, 

could result in fuel tank explosions and 

consequent loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Wiring Modification 

Within 24 months after the effective date 

of this AD: Modify the wiring of the 

maximum level sensors of the center wing 

fuel tank, as specified in paragraph (g)(1) or 

(g)(2) of this AD, as applicable. Before further 

flight after accomplishing the modification, 

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74042 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules 

do all applicable tests and corrective actions, 

in accordance with Part 5 of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–28–078, dated 

January 23, 2014. 

(1) For post-SBF100–28–073 configuration 

airplanes: Do the modification in accordance 

with Part 1 or Part 3, as applicable, of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–28–078, dated 

January 23, 2014. 

(2) For pre-SBF100–28–073 configuration 

airplanes: Do the modification in accordance 

with Part 2 or Part 4, as applicable, of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–28–078, dated 

January 23, 2014. 

(h) Revise Maintenance or Inspection 

Program 

Within 30 days after installing the 

modification specified in paragraph (g)(1) or 

(g)(2) of this AD, as applicable: Revise the 

airplane maintenance or inspection program, 

as applicable, to incorporate the fuel 

airworthiness limitation items and critical 

design configuration control limitations 

(CDCCLs) specified in paragraph 2.L.(1)(c) of 

Fokker Service Bulletin SBF100–28–078, 

dated January 23, 2014. 

(i) No Alternative Actions, Intervals, and/or 

CDCCLs 

After accomplishing the revision required 

by paragraph (h) 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 

alternative method of compliance in 

accordance with the procedures specified in 

paragraph (j)(1) of 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, 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: 

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. 

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. 

(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 

the European Aviation Safety Agency 

(EASA); or Fokker B.V. Service’s EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0138, dated 

May 30, 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 it in Docket No. 

FAA–2015–5810. 

(2) For service information identified in 

this AD, 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 

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. 

Issued in Renton, Washington, on 

November 17, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–30007 Filed 11–25–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–5815; Directorate 

Identifier 2015–NM–039–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A330–200 and –300 series 

airplanes; and all Model A340–200, 

–300, –500, and –600 series airplanes. 

This proposed AD was prompted by 

reports that the potable water service 

panel access door was lost during flight. 

This proposed AD would require 

modifying affected potable water service 

panel access doors. We are proposing 

this AD to prevent failure of the latching 

mechanism of the potable water service 

panel access door, which could result in 

the loss of the potable water service 

panel access door during flight, and 

resultant damage to the airplane (e.g., 

damage to the trimmable horizontal 

stabilizer) that could cause loss of 

control of the airplane. 

DATES: We must receive comments on 

this proposed AD by January 11, 2016. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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. 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. 

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– 

5815; 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 proposed 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. Comments will 

be available in the AD docket shortly 

after receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

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