Federal Register / Vol. 78, No. 187 / Thursday, September 26, 2013 / Proposed Rules 59293 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0002; Directorate 

Identifier 2011–NE–42–AD] 

RIN 2120–AA64 

Airworthiness Directives; Continental 

Motors, Inc. Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM); extension of comment period. 

SUMMARY: We are extending the 

comment period to our proposed 

airworthiness directive (AD) for certain 

Continental Motors, Inc., engines with 

Airmotive Engineering Corporation 

parts manufacturer approval 

replacement cylinder assemblies 

installed. The replacement cylinder 

assemblies are marketed by Engine 

Components International Division. 

DATES: The comment period for the 

proposed rule published August 12, 

2013 (78 FR 48828) is extended. We 

must receive comments on this 

proposed AD by December 11, 2013. 

ADDRESSES: You may send your 

comments to our NPRM published in 

the Federal Register on August 12, 2013 

(78 FR 48828), 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 FURTHER INFORMATION CONTACT: 

Jurgen E. Priester, Aerospace Engineer, 

Special Certification Office, FAA, 

Rotorcraft Directorate, 2601 Meacham 

Blvd., Fort Worth, TX 76137; phone: 

817–222–5159; fax: 817–222–5785; 

email: jurgen.e.priester@faa.gov. 

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–2012–0002; Directorate Identifier 

2011–NE–42–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. 

Discussion 

This extension adds an additional 

sixty (60) days to the comment period 

in the NPRM (Directorate Identifier 

2011–NE–42–AD) published in the 

Federal Register on August 12, 2013 (78 

FR 48828). This extension also provides 

time for review and comment of the 

information we are adding to the docket. 

All other aspects of our proposed AD, as 

published in the in the Federal Register 

on August 12, 2013 (78 FR 48828), 

remain unchanged. 

Issued in Burlington, Massachusetts, on 

September 23, 2013. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–23431 Filed 9–25–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0830; Directorate 

Identifier 2013–NM–128–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 

airplanes. This proposed AD was 

prompted by a report of cracking in the 

fuselage skin underneath the satellite 

communication (SATCOM) antenna 

adapter. This proposed AD would 

require repetitive inspections of the 

visible fuselage skin and doubler if 

installed, for cracking, corrosion, and 

any indication of contact of a certain 

fastener to a bonding jumper, and repair 

if necessary. We are proposing this AD 

to detect and correct cracking and 

corrosion in the fuselage skin, which 

could lead to rapid decompression and 

loss of structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by November 12, 

2013. 

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 

review copies of the 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; 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: 

Melanie Violette, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: (425) 917–6422; 

fax: (425) 917–6590; email: 

melanie.violette@faa.gov. 

SUPPLEMENTARY INFORMATION: 


emcdonald on DSK67QTVN1PROD with PROPOSALS
59294 Federal Register / Vol. 78, No. 187 / Thursday, September 26, 2013 / Proposed Rules 

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– 

2013–0830; Directorate Identifier 2013– 

NM–128–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. 

Discussion 

We received a report of cracking and 

corrosion in the fuselage skin 

underneath the SATCOM antenna 

adapter. During a maintenance planning 

data inspection, one operator reported a 

16-inch crack under the 3-bay SATCOM 

antenna adapter plate in the crown skin 

of the fuselage on an airplane that was 

14 years old with approximately 14,000 

total flight cycles. Subsequent to this 

crack finding, the same operator 

inspected 42 other airplanes that are 

between 6 and 16 years old and found 

some local corrosion, but no other 

cracking. Cracking and corrosion in the 

fuselage skin, if not corrected, could 

lead to rapid decompression and loss of 

structural integrity of the airplane. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 777–53A0068, dated June 12, 

2013. For information on the procedures 

and compliance times, see this service 

information at http://

www.regulations.gov by searching for 

Docket No. FAA–2013–0830. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between the Proposed AD 

and the Service Information.’’ 

Differences Between the Proposed AD 

and the Service Information 

The service bulletin specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

affects 120 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection ........... Up to 36 work-hours × $85 per 

hour = $3,060 per inspection 

cycle.

$0 Up to $3,060 per inspection cycle Up to $367,200 per inspection 

cycle. 

We have received no definitive data that 

would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2013–0830; Directorate Identifier 2013– 

NM–128–AD. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 187 / Thursday, September 26, 2013 / Proposed Rules 59295 

(a) Comments Due Date 

We must receive comments by November 

12, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200, –200LR, –300, –300ER, and 

–777F series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 777–53A0068, dated June 

12, 2013. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a report of 

cracking in the fuselage skin underneath the 

satellite communication (SATCOM) antenna 

adapter. We are issuing this AD to detect and 

correct cracking and corrosion in the fuselage 

skin, which could lead to rapid 

decompression and loss of structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

(1) For Group 1–4 airplanes and Group 5, 

Configuration 3 and 4 airplanes identified in 

Boeing Alert Service Bulletin 777–53A0068, 

dated June 12, 2013: Except as required by 

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

within the applicable compliance times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 777–53A0068, 

dated June 12, 2013, do internal detailed and 

surface high frequency eddy current (HFEC) 

inspections of the visible fuselage skin, and 

doubler if installed, for cracking; do external 

detailed and surface HFEC inspections of the 

visible fuselage skin, and doubler if installed, 

for cracking, corrosion, and any indication 

that shows a contact of a certain fastener to 

a bonding jumper; and do all applicable 

repairs; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–53A0068, dated June 

12, 2013, except as required by paragraph 

(h)(3) of this AD. Thereafter, repeat the 

inspections at the applicable intervals 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 777–53A0068, 

dated June 12, 2013. Do all applicable repairs 

before further flight. 

(2) For Group 5, Configuration 1, 2, and 5 

airplanes identified in Boeing Alert Service 

Bulletin 777–53A0068, dated June 12, 2013: 

No action is required by this AD. 

(h) Exceptions to the Service Information 

(1) The ‘‘Condition Questionnaire’’ column 

in Tables 1, 5, and 9 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 777–53A0068, dated June 12, 2013, 

refers to airplanes with certain conditions ‘‘at 

the time of the original issue date of this 

service bulletin.’’ For this AD, use ‘‘as of the 

effective date of this AD’’ instead of ‘‘at the 

time of the original issue date of this service 

bulletin.’’ 

(2) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 777–53A0068, 

dated June 12, 2013, specifies a compliance 

time ‘‘after the original issue date of this 

service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(3) If any crack, corrosion, or indication 

that shows a contact of the fastener attaching 

the SATCOM lug adapter plate to the 

bonding plate is found during any inspection 

required by this AD, and Boeing Alert 

Service Bulletin 777–53A0068, dated June 

12, 2013, specifies to contact Boeing for 

repair instructions: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (i) of this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9–ANMSeattle-ACO–AMOC-Requests@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, Seattle 

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. 

(j) Related Information 

(1) For more information about this AD, 

contact Melanie Violette, Aerospace 

Engineer, Airframe Branch, ANM 120S, FAA, 

Seattle Aircraft Certification Office, 1601 

Lind Avenue SW., Renton, WA 98057 3356; 

phone: (425) 917–6422; fax: (425) 917–6590; 

email: melanie.violette@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. You 

may review copies of the 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 

September 18, 2013. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–23456 Filed 9–25–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0829; Directorate 

Identifier 2013–NM–085–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) 2010–23– 

12, which applies to certain Airbus 

Model A330–201, –202, –203, –223, 

–223F, –243, and –243F Airplanes, 

Model A330–300 series airplanes, and 

Model A340–200, A340–300, A340–500, 

and A340–600 series airplanes. AD 

2010–23–12 requires inspecting to 

determine the part number for Thales 

Avionics Angle of Attack (AoA) probes, 

and replacing any affected probe with a 

serviceable probe. Since we issued AD 

2010–23–12 we received reports that the 

AoA sensors on certain airplanes were 

modified and re-identified without 

performing the inspection to determine 

the part number; therefore, the affected 

probes were not replaced with 

serviceable probes. This proposed AD 

would add airplanes to the applicability 

and, for certain airplanes, require those 

affected probes be replaced. We are 

proposing this AD to prevent erroneous 

AoA information and consequent 

delayed activation or non-activation of 

the AoA protection systems, which, in 

combination with flight at a high angle 

of attack, could result in reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 12, 

2013. 

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 


emcdonald on DSK67QTVN1PROD with PROPOSALS