Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules 79735 

Subject National 

banks 

State 

member banks 

State 

non-member 

banks 

Federal savings 

associations 

State savings 

associations 

BHCs & FHCs 

SLHCs 

10. Rules of Procedure 

All rules under this category are included in Chart A above 

11. Safety and Soundness 

All rules under this category are included in Chart A above 

12. Securities 

All rules under this category are included in Chart A above 

Dated: December 16, 2015. 

Thomas J. Curry, 

Comptroller of the Currency. 

By order of the Board of Governors of the 

Federal Reserve System, December 11, 2015. 

Robert deV. Frierson, 

Secretary of the Board. 

Dated: December 16, 2015. 

By order of the Board of Directors. 

Federal Deposit Insurance Corporation. 

Robert E. Feldman, 

Executive Secretary. 

[FR Doc. 2015–32312 Filed 12–22–15; 8:45 am] 

BILLING CODE P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–7525; Directorate 

Identifier 2015–NM–064–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company 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 

The Boeing Company Model 747–400, 

747–400D, and 747–400F series 

airplanes; Model 757 airplanes; and 

Model 767 airplanes. This proposed AD 

was prompted by reports of 

uncommanded autopilot engagement 

events resulting in incorrect stabilizer 

trim adjustment during takeoff. This 

proposed AD would require, depending 

on the model/configuration for Model 

747 airplanes, installing an on-ground 

stabilizer autotrim inhibit system, doing 

routine functional testing of the 

automatic stabilizer trim inhibit system 

and corrective actions if necessary; for 

Model 757 airplanes and Model 767 

airplanes, installing relays and related 

wiring to open and close the flight 

control computer (FCC) analog output 

that controls the stabilizer trim 

adjustment, doing routine functional 

testing of the automatic stabilizer trim 

inhibit system, and corrective actions if 

necessary; and for Model 767–300, and 

-300F series airplanes, installing new 

operational program software (OPS) into 

the FCCs. We are proposing this AD to 

prevent stabilizer mistrim, which could 

result in a high-speed rejected takeoff 

and runway overrun, or reduced 

controllability of the airplane after 

takeoff due to insufficient pitch control. 

DATES: We must receive comments on 

this proposed AD by February 8, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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–2015– 

7525. 

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– 

7525; 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 Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Fnu 

Winarto, Aerospace Engineer, Systems 

and Equipment Branch, ANM–130S, 

FAA, Seattle Aircraft Certification 

Office (ACO), 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425– 

917–6659; fax: 425–917–6590; email: 

fnu.winarto@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–7525; Directorate Identifier 2015– 

NM–064–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 because of 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. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
79736 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules 

Discussion 

We have received reports of 

uncommanded autopilot engagement 

events resulting in incorrect stabilizer 

trim adjustment during takeoff. The 

current configuration of affected 

airplanes allows engagement of the 

autopilot while on the ground. This 

engagement can result in the stabilizer 

trim being positioned to a trim setting 

outside of the acceptable takeoff setting 

range. The root cause is unknown, but 

the erroneous autopilot engage request 

is believed to have come from the mode 

control panel (MCP) and to have been 

caused by contamination within the 

MCP. Incorrect stabilizer trim 

adjustment during takeoff, if not 

corrected, could result in a high-speed 

rejected takeoff and runway overrun, or 

reduced controllability of the airplane 

after takeoff due to insufficient pitch 

control. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following service 

information. 

• Boeing Special Attention Service 

Bulletin 747–22–2256, dated March 6, 

2015. This service information describes 

procedures for installing an on-ground 

stabilizer autotrim inhibit system, and 

doing functional testing. 

• Boeing Special Attention Service 

Bulletin 757–22–0096, dated March 23, 

2015. This service information describes 

procedures for modifying relays and 

wiring to open and close the FCC analog 

output that controls the stabilizer trim 

adjustment, and doing functional 

testing. 

• Boeing Special Attention Service 

Bulletin 767–22–0143, Revision 1, dated 

July 6, 2015. This service information 

describes procedures for modifying 

relays and wiring to open and close the 

FCC analog output that controls the 

stabilizer trim adjustment, and doing 

functional testing. 

• Boeing Special Attention Service 

Bulletin 767–22–0146, Revision 1, dated 

June 25, 2015. This service information 

describes procedures for installing new 

OPS into the FCCs. 

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 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. For information on the 

procedures and compliance times, see 

this service information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

7525. 

Differences Between This Proposed AD 

and the Service Information 

For Model 747 airplanes, this 

proposed AD would require doing postmodification routine functional testing 

of the automatic stabilizer trim inhibit 

system, and corrective actions if 

necessary, at intervals not to exceed 

1,500 flight hours. The service 

information does not require these 

actions. 

Explanation of ‘‘RC’’ Steps in Service 

Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which steps in the service 

information are required for compliance 

with an AD. Differentiating these steps 

from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The steps identified as 

Required for Compliance (RC) in any 

service information identified 

previously have a direct effect on 

detecting, preventing, resolving, or 

eliminating an identified unsafe 

condition. 

For service information that contains 

steps that are labeled as RC, the 

following provisions apply: (1) The 

steps labeled as RC, including substeps 

under an RC step and any figures 

identified in an RC step, must be done 

to comply with the AD, and an AMOC 

is required for any deviations to RC 

steps, including substeps and identified 

figures; and (2) steps not labeled 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 RC steps, 

including substeps and identified 

figures, can still be done as specified, 

and the airplane can be put back in an 

airworthy condition. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1,220 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on 

U.S. operators 

Model 747 series airplane modification 

(136 airplanes).

123 work-hours × $85 per hour = 

$10,455.

$2,714 $13,169 .................. $1,790,984. 

Model 747 series airplane functional 

test (136 airplanes).

4 work-hours × $85 per hour = $340 ..... 0 $340 per test .......... $46,240 per test. 

Model 757 series airplane modification 

(678 airplanes).

83 work-hours × $85 per hour = $7,055 3,236 $10,291 .................. $6,977,298. 

Model 757 series airplane functional 

test (678 airplanes).

3 work-hours × $85 per hour = $255 

per test.

0 $255 per test .......... $172,890 per test. 

Model 767 series airplane modification 

(406 airplanes).

121 work-hours × $85 per hour = 

$10,285.

6,076 $16,361 .................. $6,642,566. 

Model 767 series airplane software 

modification (23 airplanes).

1 work-hour × $85 per hour = $85 ........ 0 $85 ......................... $1,955. 

Model 767 series airplane functional 

test (406 airplanes).

5 work-hours × $85 per hour = $425 

per test.

0 $425 per test .......... $172,550 per test. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules 79737 

According to the manufacturer, some 

of the costs of this proposed 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 available 

costs in our cost estimate. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘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): 

The Boeing Company: Docket No. FAA– 

2015–7525; Directorate Identifier 2015– 

NM–064–AD. 

(a) Comments Due Date 

We must receive comments by February 8, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to certain The Boeing 

Company airplanes, certificated in any 

category, identified in paragraphs (c)(1) 

through (c)(4) of this AD. 

(1) Model 747–400, 747–400D, and 747– 

400F series airplanes, as identified in Boeing 

Special Attention Service Bulletin 747–22– 

2256, dated March 6, 2015. 

(2) Model 757–200, –200PF, –200CB, and 

–300 series airplanes, as identified in Boeing 

Special Attention Service Bulletin 757–22– 

0096, dated March 23, 2015. 

(3) Model 767–200, –300, –300F, and 

–400ER series airplanes, as identified in 

Boeing Special Attention Service Bulletin 

767–22–0143, Revision 1, dated July 6, 2015. 

(4) Model 767–300, and –300F series 

airplanes, as identified in Boeing Special 

Attention Service Bulletin 767–22–0146, 

Revision 1, dated June 25, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 22, Auto flight. 

(e) Unsafe Condition 

This AD was prompted by reports of 

uncommanded autopilot engagement events 

resulting in incorrect stabilizer trim 

adjustment during takeoff. We are issuing 

this AD to prevent stabilizer mistrim, which 

could result in a high-speed rejected takeoff 

and runway overrun, or reduced 

controllability of the airplane after takeoff 

due to insufficient pitch control. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Model 747 Airplane Modification and 

Repetitive Functional Testing 

For airplanes identified in paragraph (c)(1) 

of this AD: Within 24 months after the 

effective date of this AD, install new wiring 

and relays to reroute the four autotrim arm 

signals through new or existing air/ground 

determination source select switches, and do 

functional testing, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–22– 

2256, dated March 6, 2015. If the functional 

test fails, before further flight, do corrective 

actions, repeat the test, and do all applicable 

corrective actions until the functional test is 

passed, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–22– 

2256, dated March 6, 2015. Repeat the 

functional test of the automatic stabilizer 

trim system specified in step 250. of 

paragraph 3.B. of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–22–2256, dated March 

6, 2015, thereafter at intervals not to exceed 

1,500 flight hours. If any functional test fails, 

before further flight, do corrective actions, 

repeat the test, and do all applicable 

corrective actions until the functional test is 

passed, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–22– 

2256, dated March 6, 2015. 

(h) Model 757 Airplane Modification and 

Repetitive Functional Testing 

For airplanes identified in paragraph (c)(2) 

of this AD: Within 24 months after the 

effective date of this AD, install wiring to 

inhibit the automatic stabilizer trim arm 

discrete when the airplane is on ground, 

install a two-position momentary contact test 

switch in the main equipment center, and do 

the functional test and all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 757–22– 

0096, dated March 23, 2015. Repeat the 

functional test of the automatic stabilizer 

trim system and all applicable corrective 

actions specified in step 11. of paragraph 3.B. 

of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

757–22–0096, dated March 23, 2015, 

thereafter at intervals not to exceed 1,500 

flight hours. 

(i) Model 767–200, –300, –300F, and –400ER 

Series Airplane Modification and Repetitive 

Functional Testing 

For airplanes identified in paragraph (c)(3) 

of this AD: Within 24 months after the 

effective date of this AD, install relays and 

wiring to open and close the flight control 

computer (FCC) analog output that controls 

the stabilizer trim adjustment, install a 

momentary action ground test switch, and do 

the functional testing and all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 767–22– 

0143, Revision 1, dated July 6, 2015. Repeat 

the functional test of the automatic stabilizer 

trim system and all applicable corrective 

actions specified in steps 5.a. through 5.g. of 

Paragraph 3.B. of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 767–22–0143, Revision 1, 

dated July 6, 2015, thereafter at intervals not 

to exceed 1,500 flight hours. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
79738 Federal Register / Vol. 80, No. 246 / Wednesday, December 23, 2015 / Proposed Rules 

(j) Model 767–300 and –300F Series Airplane 

Modification 

For airplanes identified in paragraph (c)(4) 

of this AD: Within 16 months after the 

effective date of this AD, install new 

operational program software into the FCCs, 

in accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 767–22–0146, Revision 1, 

dated June 25, 2015. 

(k) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(1) This paragraph provides credit for 

actions required by paragraph (i) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Special 

Attention Service Bulletin 767–22–0143, 

dated March 6, 2015. 

(2) This paragraph provides credit for 

actions required by paragraph (j) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Special 

Attention Service Bulletin 767–22–0146, 

dated March 24, 2015. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (m)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (l)(4)(i) and (l)(4)(ii) apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled 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 RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(m) Related Information 

(1) For more information about this AD, 

contact Fnu Winarto, Aerospace Engineer, 

Systems and Equipment Branch, ANM–130S, 

FAA, Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6659; fax: 425– 

917–6590; email: fnu.winarto@faa.gov. 

(2) 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. 

Issued in Renton, Washington, on 

December 8, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–32055 Filed 12–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0006; Directorate 

Identifier 2013–NM–147–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for all Airbus Model A330–200, A330– 

200 Freighter, A330–300, A340–200, 

and A340–300 series airplanes. The 

NPRM proposed to require inspecting 

certain trimmable horizontal stabilizer 

actuators (THSAs) to determine the 

number of total flight cycles the THSA 

has accumulated, and replacing the 

THSA if necessary. The NPRM was 

prompted by the results of endurance 

qualification tests on the THSA, which 

revealed a partial loss of the no-back 

brake (NBB) efficiency in specific load 

conditions. This action revises the 

NPRM by adding airplanes to the 

proposed applicability, reducing the 

proposed compliance times for 

replacing affected THSAs, and revising 

the definition of a serviceable THSA. 

We are proposing this supplemental 

NPRM (SNPRM) to detect and correct 

premature wear of the carbon friction 

disks on the NBB of the THSA, which 

could lead to reduced braking efficiency 

in certain load conditions, and, in 

conjunction with the inability of the 

power gear train to keep the ball screw 

in its last commanded position, could 

result in uncommanded movements of 

the trimmable horizontal stabilizer and 

loss of control of the airplane. Since 

these actions impose an additional 

burden over those proposed in the 

NPRM, we are reopening the comment 

period to allow the public the chance to 

comment on these proposed changes. 

DATES: We must receive comments on 

this SNPRM by February 8, 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–2014– 

0006; 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 Office 

(telephone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS