Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules 56405 

PART 327—IMPORTED PRODUCTS 

■ 1. The authority citation for part 327 

continues to read as follows: 

Authority: 21 U.S.C. 601–695; 7 CFR 2.18, 

2.53. 

§ 327.2 [Amended] 

■ 2. Amend § 327.2 by adding Namibia 

in alphabetical order to the list of 

countries in paragraph (b). 

Done at Washington, DC, on September 14, 

2015. 

Alfred V. Almanza, 

Acting Administrator. 

[FR Doc. 2015–23455 Filed 9–17–15; 8:45 am] 

BILLING CODE 3410–DM–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3631; Directorate 

Identifier 2015–NM–060–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; Model A330–200 Freighter 

series airplanes; and Model A340–200, 

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

This proposed AD was prompted by 

reports of chafed wiring at the upper left 

corner of the cockpit door. The affected 

wire bundle was not grounded on the 

cockpit door frame. This proposed AD 

would require modifying the cockpit 

door frame structure, installing bondingleads to the upper cockpit door frame, 

and modifying the upper cockpit door 

plate cover. We are proposing this AD 

to prevent electrical shock injury to 

persons contacting the cockpit door. 

DATES: We must receive comments on 

this proposed AD by November 2, 2015. 

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– 

3631; 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 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–3631; Directorate Identifier 

2015–NM–060–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 2015–0037, dated March 2, 

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 and –300 series 

airplanes; Model A330–200 Freighter 

series airplanes; and Model A340–200, 

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

The MCAI states: 

An operator has reported chafed wiring at 

the upper left corner of the cockpit door. The 

investigation concluded that the affected 

wire bundle, which supplies a voltage of 

115V [volt] AC [alternating current], was not 

grounded on the cockpit door frame as part 

of the design of A330 and A340 aeroplanes. 

This condition, if not corrected, could 

result in injury [electrical shock], in case any 

person gets in contact with the door frame. 

Prompted by these findings, Airbus issued 

SB [service bulletin] A330–25–3534, SB 

A340–25–4349 and SB A340–25–5212 to 

provide instructions to modify the electrical 

bonding of the cockpit door. 

For the reasons described above, this 

[EASA] AD requires modification of the 

cockpit door frame structure, installation of 

bonding-leads to the upper cockpit door 

frame and modification of the upper cockpit 

door plate cover. 

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– 

3631. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. 

• Service Bulletin A330–25–3534, 

Revision 01, dated October 23, 2014. 

This service information describes 

procedures for modifying the cockpit 

door frame structure and installing 

bonding-leads to the upper cockpit door 

frame. 

• Service Bulletin A340–25–4349, 

Revision 01, dated October 27, 2014. 

This service information describes 

procedures for modifying the cockpit 

door frame structure and installing 

bonding-leads to the upper cockpit door 

frame. 

• Service Bulletin A340–25–5212, 

Revision 01, dated October 27, 2014. 

This service information describes 

procedures for modifying the cockpit 

door frame structure and installing 


tkelley on DSK3SPTVN1PROD with PROPOSALS
56406 Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules 

bonding-leads to the upper cockpit door 

frame. 

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 these same 

type designs. 

Explanation of ‘‘RC’’ Procedures and 

Tests 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 procedures and tests 

in the service information are required 

for compliance with an AD. 

Differentiating these procedures and 

tests 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 procedures and tests 

identified as Required for Compliance 

(RC) in any service information have a 

direct effect on detecting, preventing, 

resolving, or eliminating an identified 

unsafe condition. 

As specified in a NOTE under the 

Accomplishment Instructions of the 

specified service information, 

procedures and tests that are identified 

as RC in any service information must 

be done to comply with the proposed 

AD. However, procedures and 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 alternative method of compliance 

(AMOC), provided the procedures and 

tests identified as RC can be done and 

the airplane can be put back in a 

serviceable condition. Any substitutions 

or changes to procedures or tests 

identified as RC will require approval of 

an AMOC. 

Costs of Compliance 

We estimate that this proposed AD 

affects 70 airplanes of U.S. registry. 

We also estimate that it would take 

about 27 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $2,620 per 

product. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $344,050, or $4,915 

per product. 

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 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 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): 

Airbus: Docket No. FAA–2015–3631; 

Directorate Identifier 2015–NM–060–AD. 

(a) Comments Due Date 

We must receive comments by November 

2, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all the Airbus airplanes 

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

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

except airplanes on which Airbus 

Modification 203066, Modification 203074, 

or Modification 203372 has been embodied 

in production. 

(1) Model A330–201, –202, –203, –223, 

–223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes; 

all manufacturer serial numbers (MSNs); if 

modified in-service as specified in Airbus 

Service Bulletin A330–25–3161, or in 

production with Airbus Modification 50014. 

(2) Model A340–211, –212, –213, –311, 

–312, and –313 airplanes; all MSNs, if 

modified in-service as specified in Airbus 

Service Bulletin A340–25–4181, or in 

production with Airbus Modification 50014. 

(3) Model A340–541 airplanes; and Model 

A340–642 airplanes; all MSNs. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/Furnishings. 

(e) Reason 

This AD was prompted by reports of 

chafed wiring at the upper left corner of the 

cockpit door. The affected wire bundle was 

not grounded on the cockpit door frame. We 

are issuing this AD to prevent electrical 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 181 / Friday, September 18, 2015 / Proposed Rules 56407 

shock injury to persons contacting the 

cockpit door. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Door Modification and Installation 

Within 24 months after the effective date 

of this AD, modify the cockpit door frame 

structure and install bonding-leads to the 

upper cockpit door frame, in accordance with 

the Accomplishment Instructions of the 

applicable service information identified in 

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

(1) Airbus Service Bulletin A330–25–3534, 

Revision 01, dated October 23, 2014. (2) 

Airbus Service Bulletin A340–25–4349, 

Revision 01, dated October 27, 2014. (3) 

Airbus Service Bulletin A340–25–5212, 

Revision 01, dated October 27, 2014. 

(h) Cover Plate Modification of the Upper 

Flight Deck Door 

Except for airplanes on which Airbus 

Modification 52869 or Modification 53292 

has been embodied in production: Before or 

concurrently with accomplishing the 

modification required by paragraph (g) of this 

AD, modify the upper cockpit door plate 

cover, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraphs (h)(1), (h)(2), and (h)(3) of this 

AD. 

(1) Airbus Service Bulletin A330–25–3534, 

Revision 01, dated October 23, 2014. (2) 

Airbus Service Bulletin A340–25–4349, 

Revision 01, dated October 27, 2014. (3) 

Airbus Service Bulletin A340–25–5212, 

Revision 01, dated October 27, 2014. 

(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 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 

a serviceable 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 2015–0037, dated 

March 2, 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– 

2015–3631. 

(2) 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. 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 

September 11, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–23409 Filed 9–17–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0774; Directorate 

Identifier 2013–NM–154–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (SNPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

that proposed to supersede AD 2006– 

22–15 for all The Boeing Company 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747–400, 747–400D, 747– 

400F, 747SR, and 747SP series 

airplanes. AD 2006–22–15 requires 

repetitive inspections for cracking of 

certain panel webs and stiffeners of the 

nose wheel well (NWW), and corrective 

actions if necessary; and replacement of 

certain panels with new panels, which 

terminates the repetitive inspections. 

The notice of proposed rulemaking 

(NPRM) proposed to reduce a 

compliance time and add certain 

inspections and applicable repair. The 

NPRM was prompted by reports of 

fatigue cracking in the panel webs and 

stiffeners of the NWW found prior to the 

inspection threshold of AD 2006–22–15. 

This action revises the NPRM by 

specifying a repetitive inspection 

interval for a certain NWW area 

inspection. We are proposing this 

SNPRM to prevent fatigue cracking of 

the NWW side and top panels, which 

could result in a NWW depressurization 

event severe enough to reduce the 

structural integrity of the fuselage. Since 

these actions impose an additional 

burden over that 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 November 2, 2015. 

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 20590, 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 


tkelley on DSK3SPTVN1PROD with PROPOSALS