Federal Register / Vol. 78, No. 236 / Monday, December 9, 2013 / Proposed Rules 73739 

DOE is also interested in comments on 

other relevant issues that participants 

believe would affect energy 

conservation standards for these 

products, applicable test procedures, or 

the preliminary determination on the 

scope of coverage. DOE invites all 

interested parties, whether or not they 

participate in the public meeting, to 

submit in writing by January 23, 2014, 

comments and information on matters 

addressed in the Framework Document 

and on other matters relevant to DOE’s 

consideration of coverage of and 

standards for GSLs. 

The public meeting will be conducted 

in an informal, facilitated, conference 

style. There shall be no discussion of 

proprietary information, costs or prices, 

market shares, or other commercial 

matters regulated by U.S. antitrust laws. 

A court reporter will record the 

proceedings of the public meeting, after 

which a transcript will be available for 

purchase from the court reporter and 

placed on the DOE Web site at: http:// 

www1.eere.energy.gov/buildings/

appliance_standards/

product.aspx?productid=82. 

After the public meeting and the close 

of the comment period on the 

Framework Document, DOE will collect 

data, conduct the analyses as discussed 

in the Framework Document and at the 

public meeting, and review the public 

comments it receives. 

DOE considers public participation to 

be a very important part of the process 

for determining whether to establish or 

amend energy conservation standards 

and, if so, in setting those standards. 

DOE actively encourages the 

participation and interaction of the 

public during the comment period at 

each stage of the rulemaking process. 

Beginning with the Framework 

Document, and during each subsequent 

public meeting and comment period, 

interactions with and among members 

of the public provide a balanced 

discussion of the issues to assist DOE in 

the standards rulemaking process. 

Accordingly, anyone who wishes to 

participate in the public meeting, 

receive meeting materials, or be added 

to the DOE mailing list to receive future 

notices and information about this 

rulemaking should contact Ms. Brenda 

Edwards at (202) 586–2945, or via email 

at Brenda.Edwards@ee.doe.gov. 

Issued in Washington, DC, on December 2, 

2013. 

Kathleen B. Hogan, 

Deputy Assistant Secretary for Energy 

Efficiency, Energy Efficiency and Renewable 

Energy. 

[FR Doc. 2013–29166 Filed 12–6–13; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0981; Directorate 

Identifier 2013–NM–032–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 supersede 

Airworthiness Directives (ADs) 97–11– 

07 and AD 99–18–23, which apply to all 

The Boeing Company Model MD–90–30 

airplanes. AD 97–11–07 and AD 99–18– 

23 currently require revising the 

Airworthiness Limitations Section 

(ALS) of the Instructions for Continued 

Airworthiness to incorporate certain 

compliance times for principal 

structural elements (PSE) inspections 

and replacement times for safe-life 

limited parts. Since we issued AD 97– 

11–07 and AD 99–18–23, an analysis of 

data identified a need to introduce a 

new PSE requirement for the rear spar 

caps of the horizontal stabilizer. This 

proposed AD would require revising the 

maintenance or inspection program to 

incorporate the new PSE requirement 

and its associated inspections. We are 

proposing this AD to detect and correct 

fatigue cracking of PSEs and certain 

safe-life limited parts, which could 

adversely affect the structural integrity 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by January 23, 2014. 

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, 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, Washington. 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: 

Roger Durbin, Airframe Branch, ANM– 

120L, FAA, Los Angeles Aircraft 

Certification Office (ACO), 3960 

Paramount Boulevard, Lakewood, 

California 90712–4137; phone: (562) 

627–5233; fax: (562) 627–5210; email: 

roger.durbin@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–2013–0981; Directorate Identifier 

2013–NM–032–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 

On May 16, 1997, we issued AD 97– 

11–07, Amendment 39–10036 (62 FR 

27941, May 22, 1997), for all The Boeing 

Company Model MD–90–30 airplanes. 

AD 97–11–07 requires revising the 

Airworthiness Limitations Section of 

the Instructions for Continued 

Airworthiness (MD–90–30 

Airworthiness Limitations Instructions 

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73740 Federal Register / Vol. 78, No. 236 / Monday, December 9, 2013 / Proposed Rules 

(ALI)) to add principle structural 

elements (PSE) requirements. AD 97– 

11–07 resulted from analysis of data that 

identified reduced initial inspection 

thresholds, reduced repetitive 

inspection intervals for PSEs, and other 

PSEs to be added to the ALI. We issued 

AD 97–11–07 to detect and correct 

fatigue cracking, which could result in 

reduced structural integrity or reduced 

controllability of the airplane. 

On August 27, 1999, we issued AD 

99–18–23, Amendment 39–11289 (64 

FR 48284, September 3, 1999), for all 

The Boeing Company Model MD–90–30 

airplanes. AD 99–18–23 requires 

revising the Airworthiness Limitations 

Section of the Instructions for 

Continued Airworthiness (MD–90–30 

Airworthiness Limitations Instructions 

(ALI)) to incorporate certain 

replacement times for safe-life limited 

parts. AD 99–18–23 resulted from 

analysis of data that identified reduced 

replacement times for certain safe-life 

limited parts. We issued AD 99–18–23 

to prevent fatigue cracking of various 

safe-life limited parts, which could 

adversely affect the structural integrity 

of airplanes. 

Actions Since Existing AD Was Issued 

Since we issued AD 97–11–07, 

Amendment 39–10036 (62 FR 27941, 

May 22, 1997), and AD 99–18–23, 

Amendment 39–11289 (64 FR 48284, 

September 3, 1999), an analysis of data 

identified the need to introduce a new 

principle structural elements (PSE) 

requirement for the rear spar of the 

horizontal stabilizer and its associated 

inspections. 

Relevant Service Information 

We reviewed Boeing MD–90 

Airworthiness Limitations Instructions 

(ALI) Report No. MDC–94K9000, 

Revision 6, dated September 2011. For 

information on the procedures and 

compliance times, see this service 

information at http:// 

www.regulations.gov by searching for 

Docket No. FAA–2013–0981. 

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. 

This AD requires revisions to certain 

operator maintenance documents to 

include new actions (e.g., inspections). 

Compliance with these actions is 

required by 14 CFR 91.403(c). For 

airplanes that have been previously 

modified, altered, or repaired in the 

areas addressed by this AD, the operator 

may not be able to accomplish the 

actions described in the revisions. In 

this situation, to comply with 14 CFR 

91.403(c), the operator must request 

approval for an alternative method of 

compliance according to paragraph (n) 

of this proposed AD. The request should 

include a description of changes to the 

required actions that will ensure the 

continued damage tolerance of the 

affected structure. 

Proposed AD Requirements 

This proposed AD would retain all of 

the requirements of AD 97–11–07, 

Amendment 39–10036 (62 FR 27941, 

May 22, 1997), and AD 99–18–23, 

Amendment 39–11289 (64 FR 48284, 

September 3, 1999). This proposed AD 

would require revising the maintenance 

program to incorporate the new PSE 

requirement and its associated 

inspections. 

Costs of Compliance 

We estimate that this proposed AD 

affects 52 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 

Revise airworthiness limitations [retained actions from AD 97–11–07, Amendment 39– 

10036 (62 FR 27941, May 22, 1997).

1 work-hour × $85 per hour = $85 ................. $0 $85 $35,445 

Revise airworthiness limitations [retained actions from AD 99–18–23, Amendment 39– 

11289 (64 FR 48284, September 3, 1999).

1 work-hour × 85 per hour = 85 ..................... 0 85 35,445 

Revise airworthiness limitations [new proposed action].1 work-hour × 85 per hour = 85 ..................... 0 85 35,445 

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 have 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 that the 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. 

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Federal Register / Vol. 78, No. 236 / Monday, December 9, 2013 / Proposed Rules 73741 

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: 

■ a. Removing airworthiness directive 

(AD) 97–11–07, Amendment 39–10036 

(62 FR 27941, May 22, 1997), and AD 

99–18–23, Amendment 39–11289 (64 

FR 48284, September 3, 1999), and 

■ b. Adding the following new AD: 

The Boeing Company: Docket No. FAA– 

2013–0981; Directorate Identifier 2013–NM– 

032–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by January 23, 2014. 

(b) Affected ADs 

This AD supersedes AD 97–11–07, 

Amendment 39–10036 (62 FR 27941, May 22, 

1997), and AD 99–18–23, Amendment 39– 

11289 (64 FR 48284, September 3, 1999). 

(c) Applicability 

This AD applies to all The Boeing 

Company Model MD–90–30 airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 51, Standard Practices/

Structures; Code 55, Stabilizers. 

(e) Unsafe Condition 

This AD was prompted by an analysis of 

data that identified a need to introduce a new 

principal structural elements (PSE) 

requirement for the rear spar caps of the 

horizontal stabilizer. We are issuing this AD 

to detect and correct fatigue cracking of PSEs 

and certain safe-life limited parts, which 

could adversely affect the structural integrity 

of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Revision of Airworthiness 

Limitations of Principal Structural Elements 

This paragraph restates the requirements of 

paragraph (a) of AD 97–11–07, Amendment 

39–10036 (62 FR 27941, May 22, 1997). 

Within 180 days after June 26, 1997 (the 

effective date of AD 97–11–07, Amendment 

39–10036 (62 FR 27941, May 22, 1997)), 

revise the Airworthiness Limitations Section 

of the Instructions for Continued 

Airworthiness (Airworthiness Limitations 

Instructions (ALI), McDonnell Douglas 

Report No. MDC–94K9000, dated November 

1994) to incorporate the Item, Location, and 

Inspection Interval of principal structural 

elements identified in paragraphs (g)(1) 

through (g)(3) of this AD. This may be 

accomplished by inserting a copy of Revision 

1 of the ALI, dated January 1995; or a copy 

of this AD into the ALI. 

(1) For Item 53.30.02.3 at Skin Panels, STA 

237 to 1395 Fuselage Skin in Constant 

Section from Longeron 3 Left to Longeron 3 

Right: Initial Interval at 60,000 landings. 

Repeat the inspection thereafter at intervals 

not to exceed 11,000 landings. 

(2) For Item 53.30.02.4 at Skin Panels, STA 

237 to 1395 Fuselage Hoop Skin Splice in 

Constant Section from Longeron 5 Left to 

Longeron 5 Right: Initial Interval at 60,000 

landings. Repeat the inspection thereafter at 

intervals not to exceed 30,000 landings. 

(3) For Item 54.10.04.1 at Thrust Bulkhead, 

Pylon—STA Yn 170.5—Rear Spar and Engine 

Thrust Support Fitting (Upper and Lower): 

Initial Interval at 15,000 landings. Repeat the 

inspection thereafter at intervals not to 

exceed 4,500 landings. 

(h) Retained Revision of Airworthiness 

Limitations 

(1) This paragraph restates the 

requirements of paragraph (b) of AD 97–11– 

07, Amendment 39–10036 (62 FR 27941, May 

22, 1997). Within 180 days after June 26, 

1997 (the effective date of AD 97–11–07, 

Amendment 39–10036 (62 FR 27941, May 22, 

1997)), revise the Airworthiness Limitations 

Section of the Instructions for Continued 

Airworthiness (Airworthiness Limitations 

Instructions (ALI), McDonnell Douglas 

Report No. MDC–94K9000, dated November 

1994) to incorporate the Item, Location, and 

Inspection Interval of principal structural 

element specified in paragraph (h)(2) of this 

AD. This may be accomplished by inserting 

a copy of Revision 2 to the ALI, dated July 

1996, or a copy this AD into the ALI or 

Airworthiness Limitations Section. 

(2) For Item 55.13.01.1 at Plates/Skin— 

Upper STA Xh 27.2 Left to Xh 27.2 Right— 

Upper Aft Skin Plank with Integral Stringers 

from Xh 7.234 to Xh 26.859: Initial Interval 

at 60,000 landings. Repeat the inspection 

thereafter at intervals not to exceed 8,100 

landings. 

(i) Retained Restriction on Alternative 

Inspections and Inspection Intervals 

This paragraph restates the restriction on 

alternative inspections and inspection 

intervals required by paragraph (c) of AD 97– 

11–07, Amendment 39–10036 (62 FR 27941, 

May 22, 1997). Except as provided by 

paragraphs (l) and (n) of this AD: 

After the actions required by paragraphs (g) 

and (h) of this AD have been accomplished, 

no alternative inspections or inspection 

intervals may be approved for the parts 

specified in paragraphs (g) and (h) of this AD. 

(j) Retained Revision of Airworthiness 

Limitations of Safe-Life Limited Parts: 

This paragraph restates the requirements of 

paragraph (a) of AD 99–18–23, Amendment 

39–11289 (64 FR 48284, September 3, 1999). 

Within 180 days after October 8, 1999 (the 

effective date of AD 99–18–23, Amendment 

39–48284 (64 FR 48284, September 3, 1999)), 

revise the Airworthiness Limitations Section 

of the Instructions for Continued 

Airworthiness (Airworthiness Limitations 

Instructions (ALI), McDonnell Douglas 

Report No. MDC–94K9000, dated November 

1994) to incorporate the Part Number, Item, 

and Mandatory Replacement Time of certain 

safe-life limited parts by inserting a copy of 

Revision 3, to the ALI, dated November 1997, 

into the ALI. 

(k) Retained Restriction on Alternative 

Inspections and Inspection Intervals 

This paragraph restates the restriction on 

alternative inspections and inspection 

intervals required by paragraph (b) of AD 99– 

18–23, Amendment 39–11289 (64 FR 48284, 

September 3, 1999). Except as provided by 

paragraphs (l) and (n) of this AD: After the 

actions required by paragraph (j) of this AD 

have been accomplished, no alternative 

replacement times for the safe-life limited 

parts specified in McDonnell Douglas ALI 

Report No. MDC–94K9000, Revision 3, dated 

November 1997. 

(l) New Requirements of This AD: Revision 

of the Maintenance Program 

(1) Within 180 days after the effective date 

of this AD, revise the maintenance or 

inspection program, as applicable, to 

incorporate the tasks specified in 

Airworthiness Limitations Instructions (ALI), 

Boeing Report No. MDC–94K9000, Revision 

6, dated September 2011. The compliance 

times for the initial and repetitive intervals 

for the tasks are stated in Airworthiness 

Limitations Instructions (ALI), Boeing Report 

No. MDC–94K9000, Revision 6, dated 

September 2011. Doing the revision required 

by this paragraph terminates the revisions 

required by paragraphs (g), (h), and (j) of this 

AD. 

(m) No Alternative Actions or Intervals 

After accomplishing the revision required 

by paragraph (l) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (n) of this 

AD. 

(n) 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 (o) of this AD. 

(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 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

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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 97–11–07, 

Amendment 39–10036 (62 FR 27941, May 22, 

1997), and AD 99–18–23, Amendment 39– 

11289 (64 FR 48284, September 3, 1999), are 

approved as AMOCs for the corresponding 

provisions of this AD. 

(o) Related Information 

(1) For more information about this AD, 

contact Roger Durbin, Airframe Branch, 

ANM–120L, FAA, Los Angeles Aircraft 

Certification Office (ACO), 3960 Paramount 

Boulevard, Lakewood, California 90712– 

4137; phone: (562) 627–5233; fax: (562) 627– 

5210; email: roger.durbin@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, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on 

November 29, 2013. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–29317 Filed 12–6–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0980; Directorate 

Identifier 2013–NM–129–AD] 

RIN 2120–AA64 

Airworthiness Directives; EADS CASA 

(Type Certificate Previously Held by 

Construcciones Aeronauticas, S.A.) 

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 

EADS CASA (Type Certificate 

Previously Held by Construcciones 

Aeronauticas, S.A.) Model CN–235–300 

airplanes. This proposed AD was 

prompted by reports of reduced 

thickness of the center fuselage lower 

skin panel. This proposed AD would 

require a detailed inspection to 

determine the presence of panel 

thickness reduction, and repetitive 

nondestructive testing (NDT) 

inspections and repair if necessary. We 

are proposing this AD to detect and 

correct a reduced thickness of lower 

panel joints, which could result in 

reduced fatigue and damage tolerant 

characteristics of the lower panel joint 

to the adjacent side panels and lead to 

failure of the center fuselage lower skin 

panel, resulting in loss of control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by January 23, 2014. 

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 EADS–CASA, 

Military Transport Aircraft Division 

(MTAD), Integrated Customer Services 

(ICS), Technical Services, Avenida de 

Arago ́n 404, 28022 Madrid, Spain; 

telephone +34 91 585 55 84; fax +34 91 

585 55 05; email 

MTA.TechnicalService@casa.eads.net; 

Internet http://www.eads.net. 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; 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: 

Shahram Daneshmandi, Aerospace 

Engineer, International Branch, ANM– 

116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1112; 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–2013–0980; Directorate Identifier 

2013–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0131, 

dated June 25, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

During delivery of a spare centre fuselage 

lower skin panel to a CN–235 aeroplane 

operator, a reduced thickness of the spare 

panel was identified. The affected panel is 

used as the lower part of the fuselage 

between Frame (FR) FR13 and FR21, and 

from Stringer (STR) 24 left hand (LH) side to 

STR24 right hand (RH) side. Several CN–235 

aeroplanes could have been delivered with a 

reduced thickness panel. 

This condition, if not detected and 

corrected, could result in reduced fatigue and 

damage tolerant characteristics of the lower 

panel joint to the adjacent side panels and 

lead to failure of the part. 

To address this potentially unsafe 

condition, EADS–CASA issued All Operator 

Letter (AOL) 235–024 to provide instructions 

to determine correct centre fuselage lower 

panel configuration by accomplishing a 

detailed visual inspection (DVI) of affected 

fuselage area [for any cracking]. 

For the reason described above, this 

[EASA] AD requires a one-time inspection of 

the affected panel thickness at STR24 LH and 

STR24 RH. In case a nonconforming panel is 

found to be installed, this [EASA] AD 

requires repetitive Non Destructive Testing 

(NDT) inspections and, depending on 

findings, the accomplishment of applicable 

corrective action(s). 

maindgalligan on DSK5TPTVN1PROD with PROPOSALS