Federal Register / Vol. 80, No. 238 / Friday, December 11, 2015 / Proposed Rules 76875 

§ 1205.12 Cotton. 

The term cotton means all Upland 

cotton harvested in the United States 

and all imports of Upland cotton, 

including the Upland cotton content of 

products derived thereof. 

■ 3. In § 1205.510, revise paragraph 

(b)(3) introductory text and remove 

paragraphs (b)(3)(i) and (ii). 

The revision reads as follows: 

§ 1205.510 Levy of assessments. 

* * * * * 

(b) * * * 

(3) The following table contains 

Harmonized Tariff Schedule (HTS) 

classification numbers and 

corresponding conversion factors and 

assessments. The left column of the 

following table indicates the HTS 

classifications of imported cotton and 

cotton-containing products subject to 

assessment. The center column 

indicates the conversion factor for 

determining the raw fiber content for 

each kilogram of the HTS. HTS numbers 

for raw cotton have no conversion factor 

in the table. The right column indicates 

the total assessment per kilogram of the 

article assessed. In the event that any 

HTS number subject to assessment is 

changed and such change is merely a 

replacement of a previous number and 

has no impact on the physical 

properties, description, or cotton 

content of the product involved, 

assessments will continue to be 

collected based on the new number. 

* * * * * 

Dated: December 7, 2015. 

Rex A. Barnes, 

Associate Administrator. 

[FR Doc. 2015–31116 Filed 12–10–15; 8:45 am] 

BILLING CODE 3410–02–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–6547; Directorate 

Identifier 2014–NM–129–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2014–03– 

14, for all Airbus Model A330–200 and 

–300 series airplanes, and Model A340– 

200, –300, –500, and –600 series 

airplanes. AD 2014–03–14 currently 

requires removing bulb-type 

maintenance lights; installing a drain 

mast on certain airplanes; and installing 

muffs on connecting bleed elements on 

certain airplanes. Since we issued AD 

2014–03–14, we have determined that 

additional actions are necessary to 

address the identified unsafe condition 

for certain airplanes on which muffs are 

installed. For certain Model A340–200 

and –300 series airplanes, this proposed 

AD would also require replacing certain 

insulation sleeves with new insulation 

sleeves. We are proposing this AD to 

prevent 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 25, 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 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– 

6547; 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–2015–6547; Directorate Identifier 

2014–NM–129–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 

On January 31, 2014, we issued AD 

2014–03–14, Amendment 39–17752 (79 

FR 9382, February 19, 2014). AD 2014– 

03–14 requires actions intended to 

address an unsafe condition on all 

Airbus Model A330–200 and –300 series 

airplanes, and Model A340–200, –300, 

–500, and –600 series airplanes. 

Since we issued AD 2014–03–14, 

Amendment 39–17752 (79 FR 9382, 

February 19, 2014), the European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Union, has 

issued EASA Airworthiness Directive 

2014–0148, dated June 13, 2014 

(referred to after this the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

[Subsequent to accidents involving Fuel 

Tank Systems in flight and on ground] * * *, 

the FAA published Special Federal Aviation 

Regulation (SFAR) 88, and the Joint Aviation 

Authorities (JAA) published Interim Policy 

INT/POL/25/12. 

In response to these regulations, a global 

design review conducted by Airbus on the 

A330 and A340 type design Section 19, 

which is a flammable fluid leakage zone and 


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a zone adjacent to a fuel tank, highlighted 

potential deviations. The specific identified 

cases were that in-flight fuel drainage is 

insufficient on A340–500/–600 aeroplanes, 

maintenance lights are not qualified 

explosion-proof, and hot surfaces may exist 

on bleed systems during normal/failure 

operations. 

This condition, if not corrected, in 

combination with a fuel leak generating 

flammable vapours in the area, could result 

in a fuel tank explosion and consequent loss 

of the aeroplane. 

To address this unsafe condition, Airbus 

developed various modifications of the 

aeroplane, to be embodied in service. 

Consequently, EASA issued AD 2013–0033 

[http://ad.easa.europa.eu/blob/easa_ad_

2013_0033_superseded.pdf/AD_2013-0033_

1] [which corresponds to FAA AD 2014–03– 

14, Amendment 39–17752 (79 FR 9382, 

February 19, 2014)] to require removal of 

bulb type maintenance lights for all 

aeroplanes, installation of a drain mast 

between Frame (FR) 80 and FR83 for A340– 

500/–600 aeroplanes, and installation of 

muffs on connecting bleed elements to 

minimize hot surfaces on A330 and A340– 

200/–300 aeroplanes. 

Since that [EASA] AD was issued, it was 

reported that, for A340–200/–300 aeroplanes, 

accomplishment instructions in the 

applicable Airbus Service Bulletins (SB) for 

aeroplanes in Configurations 002 and 005 

were detailed in Configuration 003 and, 

conversely, accomplishment instructions for 

aeroplane[s] in Configuration 003 were 

detailed in Configurations 002 and 005. This 

can lead to incorrect installation of some 

insulation sleeves on the Auxiliary Power 

Unit (APU) Air Bleed Ducts between Frame 

83 and 84 for configurations 002, 003 and 

005 as per Airbus SB A340–36–4035 at 

original issue. Prompted by this finding, 

Airbus revised the affected SB with 

additional work required for aeroplanes 

included in configurations 002, 003 and 005 

that were modified using the original issue of 

the SB. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2013–0033, which is superseded, 

incorporates reference to the corrected 

Airbus SB A340–36–4035 Revision 01 and 

requires the additional work as specified in 

Airbus SB A340–36–4035 Revision 01 for 

aeroplanes already modified per the original 

SB A340–36–4035. 

The additional work is replacing the 

insulation sleeves between frames 83 

and 84 with new insulation sleeves. 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– 

6547. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service bulletins. 

• Airbus Service Bulletin A330–33– 

3041, Revision 02, dated November 7, 

2013, which describes procedures for 

removing bulb-type maintenance lights. 

• Airbus Service Bulletin A330–36– 

3037, Revision 02, dated April 7, 2014, 

which describes procedures for bleed 

leak detection loop modification of the 

auxiliary power unit (APU). 

• Airbus Service Bulletin A340–33– 

4026, Revision 02, dated November 7, 

2013, which describes procedures for 

removing bulb-type maintenance lights. 

• Airbus Service Bulletin A340–36– 

4033, Revision 02, dated May 19, 2014, 

which describes procedures for bleed 

leak detection loop modification of the 

APU. 

• Airbus Service Bulletin A340–36– 

4035, Revision 01, dated September 24, 

2013, which describes procedures for 

installing muffs on connecting bleed 

elements on certain airplanes. 

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. 

Explanation of New Service 

Information for Optional Actions 

In paragraph (i) of AD 2014–03–14, 

Amendment 39–17752 (79 FR 9382, 

February 19, 2014), an optional method 

of compliance is permitted using Airbus 

Service Bulletin A330–36–3037, 

Revision 01, dated January 24, 2013; or 

Airbus Service Bulletin A340–36–4033, 

Revision 01, dated January 28, 2013; as 

applicable. In addition, credit is given 

in paragraph (k)(3) of AD 2014–03–14 

for using Airbus Service Bulletin A340– 

36–4033, dated September 23, 2011. 

However, the MCAI only allows the 

use of Airbus Service Bulletin A330– 

36–3037, Revision 02, dated April 7, 

2014; and Airbus Service Bulletin 

A340–36–4033, Revision 02, dated May 

19, 2014; as applicable. Additional work 

is necessary for airplanes on which 

earlier revisions of this service 

information was done. 

Therefore, in paragraph (i) of this 

proposed AD, we refer to only Airbus 

Service Bulletin A330–36–3037, 

Revision 02, dated April 7, 2014; and 

Airbus Service Bulletin A340–36–4033, 

Revision 02, dated May 19, 2014; as 

applicable. 

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 RC (required for 

compliance) 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 certain 

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 43 Model A330 series airplanes 

of U.S. registry. There are no Model 

A340 airplanes registered in the U.S. 

The actions that are required by AD 

2014–03–14, Amendment 39–17752 (79 

FR 9382, February 19, 2014), and 

retained in this proposed AD take about 

21 work-hours per product, at an 

average labor rate of $85 per work-hour. 

Required parts cost about $5,219 per 

product. Based on these figures, the 

estimated cost of the actions that are 

required by AD 2014–03–14 is $7,004 

per product. 

We also estimate that it would take 

about 6 work-hours per product to 


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Federal Register / Vol. 80, No. 238 / Friday, December 11, 2015 / Proposed Rules 76877 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $279 per 

product. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $33,927, or $789 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 

removing Airworthiness Directive (AD) 

2014–03–14, Amendment 39–17752 (79 

FR 9382, February 19, 2014), and adding 

the following new AD: 

Airbus: Docket No. FAA–2015–6547; 

Directorate Identifier 2014–NM–129–AD. 

(a) Comments Due Date 

We must receive comments by January 25, 

2016. 

(b) Affected ADs 

This AD replaces AD 2014–03–14, 

Amendment 39–17752 (79 FR 9382, February 

19, 2014). 

(c) Applicability 

This AD applies to the Airbus airplanes, 

certificated in any category, specified in 

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

manufacturer serial numbers. 

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

–223, –243, –301, –302, –303, –321, –322, 

–323, –341, –342, and –343 airplanes. 

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

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

(d) Subject 

Air Transport Association (ATA) of 

America Code 26, Fire protection; 33, Lights; 

36, Pneumatic; 53, Fuselage. 

(e) Reason 

This AD results from fuel system reviews 

conducted by the airplane manufacturer. We 

are issuing this AD to prevent 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) Retained Maintenance Light Removal, 

With New Service Information 

This paragraph restates the requirements of 

paragraph (g) of AD 2014–03–14, 

Amendment 39–17752 (79 FR 9382, February 

19, 2014), with new service information. 

Except for airplanes on which Airbus 

Modification 56739 has been incorporated in 

production: Within 26 months after March 

26, 2014 (the effective date of AD 2014–03– 

14), remove the maintenance lights, in 

accordance with the Accomplishment 

Instructions of the applicable Airbus service 

information specified in paragraphs (g)(1), 

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

(1) Airbus Service Bulletin A330–33–3041, 

Revision 01, dated July 10, 2012; or Airbus 

Service Bulletin A330–33–3041, Revision 02, 

dated November 7, 2013 (for Model A330 

series airplanes). As of the effective date of 

this AD, use only Airbus Service Bulletin 

A330–33–3041, Revision 02, dated November 

7, 2013, for the actions required by paragraph 

(g) of this AD (for Model A330 series 

airplanes). 

(2) Airbus Service Bulletin A340–33–4026, 

Revision 01, dated July 10, 2012; or Airbus 

Service Bulletin A340–33–4026, Revision 02, 

dated November 7, 2013 (for Model A340– 

200 and –300 series airplanes). As of the 

effective date of this AD, use only Airbus 

Service Bulletin A340–33–4026, Revision 02, 

dated November 7, 2013, for the actions 

required by paragraph (g) of this AD (for 

Model A340–200 and –300 series airplanes). 

(3) Airbus Service Bulletin A340–33–5006, 

dated January 3, 2012 (for Model A340–500 

and –600 series airplanes). 

Note 1 to paragraph (g) of this AD: For 

Model A340–500 and –600 series airplanes, 

Airbus has issued Airbus Service Bulletin 

A340–33–5007 to introduce halogen-type 

lights which are qualified as explosion proof 

and that can be installed (at operators’ 

discretion) after removal of the nonexplosion-proof lights required by paragraph 

(g) of this AD. For Model A330 series 

airplanes and Model A340–200/–300 series 

airplanes, Airbus has issued Airbus Service 

Bulletins A330–33–3042 and A340–33–4027 

for the installation of similar lights. 

(h) Retained Insulation Muff Installation, 

With No Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2014–03–14, 

Amendment 39–17752 (79 FR 9382, February 

19, 2014), with no changes. For Model A330– 

200 and –300 series airplanes, and Model 

A340–200 and –300 series airplanes, except 

those airplanes on which Airbus 

Modification 52260 has been incorporated in 

production: Within 26 months after March 

26, 2014 (the effective date of AD 2014–03– 

14), install insulation muffs on the 

connecting auxiliary power unit (APU) bleed 

air duct, in accordance with the 

Accomplishment Instructions of the 

applicable Airbus service information 

specified in paragraphs (h)(1), (h)(2), and 

(h)(3) of this AD. 

(1) Airbus Service Bulletin A330–36–3038, 

dated January 16, 2012, for Model A330 

series airplanes on which Airbus Service 

Bulletin A330–36–3032 has been 

incorporated. 

(2) Airbus Mandatory Service Bulletin 

A330–36–3040, Revision 01, dated November 

26, 2012, for Model A330 series airplanes on 

which Airbus Service Bulletin A330–36– 

3032 has not been incorporated. 

(3) Airbus Mandatory Service Bulletin 

A340–36–4035, Revision 01, dated 

September 24, 2013, for Model A340 series 

airplanes. 

(i) Retained Alternative Action to Paragraph 

(h) of This AD 

This paragraph restates the alternative 

action specified in paragraph (i) of AD 2014– 

03–14, Amendment 39–17752 (79 FR 9382, 

February 19, 2014), with new service 

information. For Model A330 series airplanes 


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76878 Federal Register / Vol. 80, No. 238 / Friday, December 11, 2015 / Proposed Rules 

on which the modification described in 

Airbus Service Bulletin A330–36–3032 has 

not been incorporated, and for Model A340 

series airplanes: Doing the bleed leak 

detection loop modification of the APU, in 

accordance with the Accomplishment 

Instructions of the applicable Airbus service 

bulletin specified in paragraphs (i)(1) and 

(i)(2) of this AD, is an acceptable alternative 

to the actions required by paragraph (h) of 

this AD, provided the modification is 

accomplished within 26 months after March 

26, 2014 (the effective date of AD 2014–03– 

14). 

(1) Airbus Service Bulletin A330–36–3037, 

Revision 02, dated April 7, 2014. 

(2) Airbus Service Bulletin A340–36–4033, 

Revision 02, dated May 19, 2014. 

(j) Retained Drain Mast Installation, With No 

Changes 

This paragraph restates the requirements of 

paragraph (j) of AD 2014–03–14, Amendment 

39–17752 (79 FR 9382, February 19, 2014), 

with no changes. For Model A340–500 and 

–600 series airplanes, except those on which 

Airbus Modification 54636 or 54637 has been 

incorporated in production: Within 26 

months after March 26, 2014 (the effective 

date of AD 2014–03–14), install a drain mast 

between frame (FR) 80 and FR 83, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A340–53–5031, Revision 02, dated 

August 3, 2011. 

(k) New Requirement of This AD: 

Replacement of Certain Insulation Sleeves 

For Model A340 series airplanes in 

configurations 002, 003, and 005, as 

described in Airbus Service Bulletin A340– 

36–4035, dated September 18, 2012, that 

have been modified before the effective date 

of this AD in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A340–36–4035, dated 

September 18, 2012: Within 14 months after 

the effective date of this AD, replace the 

insulation sleeves between frames 83 and 84 

with new insulation sleeves, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A340–36–4035, 

Revision 01, dated September 24, 2013. 

(l) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (g) of this AD, 

if those actions were performed before March 

26, 2014 (the effective date of AD 2014–03– 

14, Amendment 39–17752 (79 FR 9382, 

February 19, 2014)), using Airbus Service 

Bulletin A330–33–3041, dated January 3, 

2012; or Airbus Service Bulletin A340–33– 

4026, dated January 3, 2012; as applicable; 

which are not incorporated by reference in 

this AD. 

(2) This paragraph provides credit for 

actions required by paragraph (h) of this AD, 

if those actions were performed before March 

26, 2014 (the effective date of AD 2014–03– 

14, Amendment 39–17752 (79 FR 9382, 

February 19, 2014)), using Airbus Service 

Bulletin A330–36–3040, dated September 18, 

2012, which is not incorporated by reference 

in this AD. 

(3) For Model A340 series airplanes in 

configurations 001 and 004, as described in 

Airbus Service Bulletin A340–36–4035, 

dated September 18, 2012: This paragraph 

provides credit for actions required by 

paragraph (h) of this AD, if those actions 

were performed before the effective date of 

this AD using Airbus Service Bulletin A340– 

36–4035, dated September 18, 2012, which is 

not incorporated by reference in this AD. 

(4) This paragraph provides credit for 

actions required by paragraph (j) of this AD, 

if those actions were performed before March 

26, 2014 (the effective date of AD 2014–03– 

14, Amendment 39–17752 (79 FR 9382, 

February 19, 2014)), using Airbus Service 

Bulletin A340–53–5031, dated July 31, 2006; 

or Airbus Service Bulletin A340–53–5031, 

Revision 01, dated January 10, 2008; as 

applicable; which are not incorporated by 

reference in this AD. 

(m) 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. 

(i) 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. 

(ii) AMOCs approved previously for 

paragraphs (g) and (h) of AD 2014–03–14, 

Amendment 39–17752 (79 FR 9382, February 

19, 2014), are approved as AMOCs for the 

corresponding provisions of paragraphs (g) 

and (h) of this AD. 

(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 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. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0148, dated 

June 13, 2014, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2015–6547. 

(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 

December 4, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–31210 Filed 12–10–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–6548; Directorate 

Identifier 2015–NM–114–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 787–8 and 

787–9 airplanes equipped with General 

Electric engines. This proposed AD was 

prompted by reports of cracking in 

barrel nuts on a forward engine mount 

of Model 747–8 airplanes, which shares 

a similar design to the forward engine 

mount of Model 787–8 and 787–9 

airplanes. This proposed AD would 

require, for certain airplanes, 

replacement of the four barrel nuts of 

the forward engine mount on each 

engine. For certain other airplanes, this 

proposed AD would require an 

inspection to determine if any forward 


jstallworth on DSK7TPTVN1PROD with PROPOSALS