Federal Register / Vol. 80, No. 146 / Thursday, July 30, 2015 / Proposed Rules 45457 

accordance with Part 5 of the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3515, dated 

December 19, 2007, or Boeing 707 Alert 

Service Bulletin A3515, Revision 1, dated 

October 10, 2014; or replace the chord, in 

accordance with Part 6 of the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3515, dated 

December 19, 2007, or Boeing 707 Alert 

Service Bulletin A3515, Revision 1, dated 

October 10, 2014. 

(m) Retained Supplemental Structural 

Inspection Document Inspections 

This paragraph restates the actions 

required by paragraph (m) of AD 2012–17– 

13, Amendment 39–17176 (77 FR 55681, 

September 11, 2012). For all airplanes: 

Within 180 days or 1,000 flight cycles after 

October 16, 2012 (the effective date of AD 

2012–17–13), whichever occurs first, do the 

inspections of the applicable structurally 

significant items specified in and in 

accordance with the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3516, dated April 4, 2008. If any 

cracking is found, before further flight, repair 

in accordance with the procedures specified 

in paragraph (r) of this AD. The inspections 

required by AD 85–12–01 R1, Amendment 

39–5439 (51 FR 36002, October 8, 1986), are 

still required, except, as of October 16, 2012 

(the effective date of AD 2012–17–13), the 

flight-cycle interval for the repetitive 

inspections specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing 707 Alert Service 

Bulletin A3516, dated April 4, 2008, must be 

counted in accordance with the requirements 

of paragraph (g) of this AD. 

(n) Retained Exception to Certain Service 

Information: Contacting FAA for Crack 

Repair 

This paragraph restates the actions 

required by paragraph (n) of AD 2012–17–13, 

Amendment 39–17176 (77 FR 55681, 

September 11, 2012), with revised service 

information. If any cracking is found during 

any inspection required by this AD, and 

Boeing 707 Alert Service Bulletin A3515, 

dated December 19, 2007, or Boeing 707 

Alert Service Bulletin A3515, Revision 1, 

dated October 10, 2014, specifies to contact 

Boeing for appropriate action: Before further 

flight, repair the cracking using a method 

approved in accordance with the procedures 

specified in paragraph (r) of this AD. 

(o) Retained Exception to Certain Service 

Information: Nondestructive Test 

Compliance Procedures 

This paragraph restates the requirements of 

paragraph (o) of AD 2012–17–13, 

Amendment 39–17176 (77 FR 55681, 

September 11, 2012), with revised service 

information. Where Boeing 707 Alert Service 

Bulletin A3515, dated December 19, 2007, or 

Boeing 707 Alert Service Bulletin A3515, 

Revision 1, dated October 10, 2014, specifies 

that operators ‘‘refer to’’ nondestructive test 

(NDT) procedures, the procedures must be 

done in accordance with the service 

information identified in paragraphs (o)(1), 

(o)(2), and (o)(3) of this AD, as applicable. 

(1) Figure 20, ‘‘Electrical Conductivity 

Measurement for Aluminum,’’ of Subject 51– 

00–00, ‘‘Structures-General,’’ of Part 6—Eddy 

Current, of the Boeing 707/720 

Nondestructive Test Manual, Document D6– 

48023, Revision 118, dated July 15, 2011. 

(2) Subject 55–10–07, ‘‘Horizontal 

Stabilizer,’’ of Part 6—Eddy Current, of the 

Boeing 707/720 Nondestructive Test Manual, 

Document D6–48023, Revision 118, dated 

July 15, 2011. 

(3) Subject 51–01–00, ‘‘Orientation and 

Preparation for Testing’’ of Part 1—General, 

of the Boeing 707/720 Nondestructive Test 

Manual, Document D6–48023, Revision 118, 

dated July 15, 2011. 

(p) Retained Parts Installation Prohibition 

As of October 16, 2012 (the effective date 

of AD 2012–17–13, Amendment 39–17176 

(77 FR 55681, September 11, 2012)), no 

person may install any horizontal stabilizer 

assembly with any chord segment having a 

part number other than that identified in 

paragraph 2.C.2. of Boeing 707 Alert Service 

Bulletin A3515, dated December 19, 2007, or 

Boeing 707 Alert Service Bulletin A3515, 

Revision 1, dated October 10, 2014, on any 

airplane. 

(q) New Replacement of 7079 Aluminum 

Components 

Within 48 months after the effective date 

of this AD: Replace all 7079 aluminum chord 

segments of the upper and lower chords 

installed on the horizontal stabilizer with 

7075 aluminum chord segments, in 

accordance with Part 6 of the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3515, Revision 1, 

dated October 10, 2014. Within 4,000 flight 

cycles after accomplishing the replacements 

required by this paragraph, repeat the 

inspection required by paragraph (j) of this 

AD; and repeat the inspection thereafter at 

intervals not to exceed 500 flight cycles, and 

before further flight after any replacement of 

the horizontal stabilizer. 

(r) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 (s)(1) of this AD. Information may 

be emailed to: 9-ANM-LAACO-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 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 2012–17–13, 

Amendment 39–17176 (77 FR 55681, 

September 11, 2012), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(s) Related Information 

(1) For more information about this AD, 

contact Chandra Ramdoss, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles Aircraft Certification 

Office (ACO), 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5239; fax: 562–627–5210; email: 

chandraduth.ramdoss@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, CA 90846–0001; 

telephone 206–544–5000, extension 2; fax 

206–766–5683; 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 July 16, 

2015. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–18559 Filed 7–29–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2964; Directorate 

Identifier 2014–NM–206–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 A319, A320, and A321 

series airplanes. This proposed AD is 

intended to complete certain mandated 

programs intended to support the 

airplane reaching its limit of validity 

(LOV) of the engineering data that 

support the established structural 

maintenance program. This proposed 

AD would require reinforcing the 

forward pressure bulkhead at a certain 

stringer on both the left-hand and righthand sides, and related investigative 

and corrective actions if necessary. We 

are proposing this AD to prevent fatigue 

cracking of the forward pressure 


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bulkhead, which could result in 

reduced structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by September 14, 

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, 

Airworthiness Office—EIAS, 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– 

2964; 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

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–2015–2964; Directorate Identifier 

2014–NM–206–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 

As described in FAA Advisory 

Circular 120–104 (http://www.faa.gov/

documentLibrary/media/Advisory_

Circular/120–104.pdf), several programs 

have been developed to support 

initiatives that will ensure the 

continued airworthiness of aging 

airplane structure. The last element of 

those initiatives is the requirement to 

establish a LOV of the engineering data 

that support the structural maintenance 

program under 14 CFR 26.21. This 

proposed AD is the result of an 

assessment of the previously established 

programs by the design approval holder 

(DAH) during the process of establishing 

the LOV for Model A319, A320, and 

Model A321 series airplanes. The 

actions specified in this proposed AD 

are necessary to complete certain 

programs to ensure the continued 

airworthiness of aging airplane structure 

and to support an airplane reaching its 

LOV. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0209, dated September 

19, 2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on all Model A319, 

A320, and Model A321 series airplanes. 

The MCAI states: 

During the A320 fatigue test campaign for 

Extended Service Goal (ESG), it was 

determined that fatigue damage could 

develop on the forward pressure bulkhead at 

Frame (FR) 35 on left hand (LH) side and 

right hand (RH) side. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To address this potential unsafe condition, 

a reinforcement modification was developed, 

which has been published through Airbus 

Service Bulletin (SB) A320–53–1268 for inservice application to allow aeroplanes to 

operate up to the new ESG limit. 

For the reasons described above, this 

[EASA] AD requires reinforcement of the 

centre fuselage forward pressure bulkhead at 

FR35. 

The forward pressure bulkhead 

reinforcement includes related 

investigative actions of measuring the 

diameters of certain fastener holes, and 

if they are not oversized, doing a 

rotating probe inspection for cracking of 

the fastener holes. 

Required corrective actions include 

cold expanding crack-free holes or 

repairing oversize or cracked holes by 

using a method approved by the FAA, 

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– 

2964. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–53–1268, Revision 02, dated July 

15, 2014. The service information 

describes procedures for reinforcing the 

forward pressure bulkhead at frame 35, 

stringer 30, on both the left-hand and 

right-hand sides; and repairs. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 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 

Directives Implementation Aviation 


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Rulemaking Committee (AD 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 actions specified in the 

service information identified 

previously include procedures and tests 

that are identified as RC (required for 

compliance) because these procedures 

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 48 airplanes of U.S. registry. 

We also estimate that it would take 

about 21 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 $85,680, or $1,785 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–2015–2964; 

Directorate Identifier 2014–NM–206–AD. 

(a) Comments Due Date 

We must receive comments by September 

14, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

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

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

all manufacturer serial numbers. 

(1) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes. 

(2) Airbus Model A320–211, –212, –214, 

–231, –232, and –233 airplanes. 

(3) Airbus Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD is intended to complete certain 

mandated programs intended to support the 

airplane reaching its limit of validity (LOV) 

of the engineering data that support the 

established structural maintenance program. 

We are issuing this AD to prevent fatigue 

cracking of the forward pressure bulkhead, 

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) Reinforcement, Related Investigative 

Actions, and Corrective Actions 

Before the accumulation of 48,000 total 

flight cycles or 96,000 total flight hours, 

whichever occurs first: Reinforce the forward 

pressure bulkhead at frame 35, stringer 30, on 

both the left-hand and right-hand sides; and 

do all applicable related investigative and 

corrective actions; in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1268, Revision 02, 

dated July 15, 2014, except as provided by 

paragraph (h) of this AD. Do all corrective 

actions before further flight. 

(h) Exception to Service Information 

Specifications 

Although Airbus Service Bulletin A320– 

53–1268, Revision 02, dated July 15, 2014, 

specifies to contact Airbus for repair 

instructions, and specifies that action as 

‘‘RC’’ (Required for Compliance), this AD 

requires 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). 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Airbus Service Bulletin 

A320–53–1268, dated January 8, 2013; or 

Airbus Service Bulletin A320–53–1268, 

Revision 01, dated July 23, 2013. This service 


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information is not incorporated by reference 

in this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; 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 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (h) 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 

a serviceable 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) EASA AD 

2014–0209, dated September 19, 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–2015–2964. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 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 July 17, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–18534 Filed 7–29–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2966; Directorate 

Identifier 2015–NM–051–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 

airplanes. This proposed AD was 

prompted by a report of fuel leaking 

onto the hot exhaust portion of an 

engine as a result of an un-intended leak 

path from the leading edge through the 

pylons. This proposed AD would 

require installing new seal dams in the 

inboard and outboard corners of the aft 

pylon frame on the left and right 

engines, including an inspection for 

damage of the outboard blade seal and 

applicable corrective actions. We are 

proposing this AD to prevent fuel 

leaking from an unintended drain path 

from the leading edge through the 

pylons and onto the hot engine parts or 

brakes, which could lead to a major 

ground fire. 

DATES: We must receive comments on 

this proposed AD by September 14, 

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: 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– 

2966. 

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– 

2966; 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: 

Sherry Vevea, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office 

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

WA 98057–3356; phone: 425–917–6514; 

fax: 425–917–6590; email: 

sherry.vevea@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– 

2015–2966; Directorate Identifier 2015– 

NM–051–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. 


Lhorne on DSK7TPTVN1PROD with PROPOSALS