81786 Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules 

Issued in Washington, DC, on December 

22, 2015. 

Kathleen B. Hogan, 

Deputy Assistant Secretary for Energy 

Efficiency, Energy Efficiency and Renewable 

Energy. 

[FR Doc. 2015–32893 Filed 12–30–15; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8134; Directorate 

Identifier 2014–NM–256–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 all 

Airbus Model A300 series airplanes; 

and Airbus Model A300 B4–600, B4– 

600R, and F4–600R series airplanes; and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes). This 

proposed AD was prompted by a report 

of cracking of the lower tension bolt 

area at the rib one junction (both sides) 

of the lower wing. This proposed AD 

would require repetitive inspections for 

cracking of the fasteners and of the 

fitting around the fastener holes at the 

Frame (FR) 40 lower wing location, and 

corrective actions if necessary. We are 

proposing this AD to detect and correct 

crack initiation of the fittings of the 

FR40 lower wing locations, which could 

result in reduced structural integrity of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by February 16, 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—EAW, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@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– 

8134; or in person at the Docket 

Operations office 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

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–2015–8134; Directorate Identifier 

2014–NM–256–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 2014–0272, dated December 

12, 2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for all Airbus 

Model A300 series airplanes; and 

Airbus Model A300 B4–600, B4–600R, 

and F4–600R series airplanes; and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes). The MCAI 

states: 

Following the A300–600 Extended Service 

Goal (ESG2) exercise, specific inspections for 

cracks were performed in fittings of frame 

(FR) 40, in areas not covered by any existing 

task. 

Findings were identified on an A300–600 

aeroplane withdrawn from service in the 

lower tension bolt area at rib one junction 

(both sides). 

This condition, if not detected and 

corrected, could lead to crack initiation, 

affecting the structural integrity of the 

aeroplane. 

To address this potential unsafe condition, 

an inspection programme was developed for 

the fitting around the fastener holes located 

at FR40 lower wing junction, left-hand (LH) 

and right-hand (RH) sides. 

For the reasons described above, this 

[EASA] AD requires repetitive High 

Frequency Eddy Current (HFEC) inspections 

and rototest inspections of the fitting around 

the fastener holes located at FR40 lower wing 

junction and, depending on findings, 

accomplishment of a repair. 

The corrective actions include a 

repair 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). 

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– 

8134. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Airbus Service Bulletins 

A300–57–0257 and A300–57–6115, both 

dated April 4, 2014. The service 

information describes procedures for 

repetitive inspections for cracking of the 

fasteners and of the fitting around the 

fastener holes at the FR40 lower wing 

location. 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 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules 81787 

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 ‘‘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 an 

airworthy 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 166 airplanes of U.S. registry. 

We also estimate that it would take 

about 12 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $169,320, or $1,020 per product. 

We have received no definitive data 

that would enable us to provide a cost 

estimate 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): 

Airbus: Docket No. FAA–2015–8134; 

Directorate Identifier 2014–NM–256–AD. 

(a) Comments Due Date 

We must receive comments by February 

16, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus airplanes 

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

this AD, certificated in any category. 

(1) Airbus Model A300 B2–1A, B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes. 

(2) Airbus Model A300 B4–601, B4–603, 

B4–620, B4–622, B4–605R, B4–622R, F4– 

605R, F4–622R, and C4–605R Variant F 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a report of 

cracking of the lower tension bolt area at rib 

one junction (both sides) of the lower wing. 

We are issuing this AD to detect and correct 

crack initiation of the fittings of the Frame 

(FR) 40 lower wing locations, which could 

result in reduced structural integrity of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive High Frequency Eddy Current 

Inspections 

Within 1,000 flight hours after the effective 

date of this AD: Do a high frequency eddy 

current (HFEC) inspection for cracking of 

fasteners 1 through 3 at the left-hand and 

right-hand sides of the FR40 lower junction, 

and of the fitting around the fastener holes, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletins 

A300–57–0257 (for Model A300 B2–1A, B2– 

1C, B2K–3C, B2–203, B4–2C, B4–103, and 

B4–203 airplanes) or A300–57–6115 (for 

Model A300 B4–601, B4–603, B4–620, B4– 

622, B4–605R, B4–622R, F4–605R, F4–622R, 

and C4–605R Variant F airplanes), both dated 

April 4, 2014, as applicable. If no cracking is 

found, repeat the HFEC inspection at 

intervals not to exceed 1,000 flight hours 

until a rototest inspection required by 

paragraph (h)(2) of this AD has been done. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
81788 Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules 

(h) Repetitive Rototest Inspections 

Within 36 months after the effective date 

of this AD: Remove the fasteners and 

measure the diameter of the fastener holes; 

and, before further flight, do the applicable 

actions required by paragraph (h)(1) or (h)(2) 

of this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–0257 (for Model 

A300 B2–1A, B2–1C, B2K–3C, B2–203, B4– 

2C, B4–103, and B4–203 airplanes) or A300– 

57–6115 (for Model A300 B4–601, B4–603, 

B4–620, B4–622, B4–605R, B4–622R, F4– 

605R, F4–622R, and C4–605R Variant F 

airplanes), as applicable. 

(1) If one or more of the hole diameters is 

outside the tolerance of the nominal 

diameter, and outside the tolerance of the 

first and second oversize: Do the applicable 

corrective actions required by paragraph (i) of 

this AD. 

(2) If all of the hole diameters are within 

the tolerance of the nominal diameter or the 

first or second oversize: Do detailed and 

rototest inspections for cracking of the 

fastener holes at the left-hand and right-hand 

sides of the FR40 lower junction, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletins 

A300–57–0257 (for Model A300 B2–1A, B2– 

1C, B2K–3C, B2–203, B4–2C, B4–103, and 

B4–203 airplanes) or A300–57–6115 (for 

Model A300 B4–601, B4–603, B4–620, B4– 

622, B4–605R, B4–622R, F4–605R, F4–622R, 

and C4–605R Variant F airplanes), both dated 

April 4, 2014, as applicable. If no cracking is 

found, before further flight, install new 

fasteners of the same diameter in special 

clearance fit for fasteners 1 through 3 of the 

FR40 lower junction, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletins A300–57–0257 or A300– 

57–6115, both dated April 4, 2014, as 

applicable. Repeat the rototest inspection 

thereafter at intervals not to exceed 7,000 

flight cycles. Accomplishment of a rototest 

inspection required by this paragraph 

terminates the repetitive HFEC inspections 

required by paragraph (g) of this AD. 

(i) Corrective Actions 

If, during any inspection required by this 

AD, any crack is found, or one or more of the 

hole diameters are outside the tolerance of 

the nominal diameter: Repair before further 

flight 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). 

(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, 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; 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): Except 

as required by paragraph (i) of this AD: 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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2014–0272, dated 

December 12, 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–2015–8134. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

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

93 44 51; email account.airworth-eas@

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 21, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–32848 Filed 12–30–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8130; Directorate 

Identifier 2014–NM–175–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 777–200 

and –300 series airplanes equipped with 

Pratt and Whitney engines. This 

proposed AD was prompted by reports 

of blocked drain lines at the engine 

forward strut that caused flammable 

fluid to accumulate in a flammable 

leakage zone. This proposed AD would 

require doing the following actions on 

the left strut and right strut: A one-time 

cleaning of certain forward strut drain 

lines; installing new forward strut drain 

lines and insulation blankets; a leak 

check of the forward strut drain lines; 

and repair if any leak is found. This 

proposed AD would also require 

revising the maintenance or inspection 

program, as applicable, to incorporate a 

certain airworthiness limitation. We are 

proposing this AD to prevent blockage 

of forward strut drain lines, which 

could cause flammable fluids to collect 

in the forward strut area and potentially 

cause an uncontrolled fire or cause 

failure of engine attachment structure 

and consequent airplane loss. 

DATES: We must receive comments on 

this proposed AD by February 16, 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, 


tkelley on DSK3SPTVN1PROD with PROPOSALS