20824 Federal Register / Vol. 79, No. 71 / Monday, April 14, 2014 / Proposed Rules 

fasteners, in accordance with the 

Accomplishment Instructions of Lockheed L– 

1011 Service Bulletin 093–53–105, Revision 

3, dated May 31, 2013. 

(2) If two or more adjacent fittings on both 

sides of the cracked fittings or bonded splice 

tabs/fasteners are determined to be free of 

cracks by the ECSS inspection required by 

paragraph (o) of this AD, the related 

investigative actions (inspections of the inner 

and outer tee caps) required by paragraph (n) 

of this AD may also be deferred until the 

cracked fittings are replaced as required by 

paragraph (q)(1) of this AD, but no later than 

before the accumulation of 20,800 total flight 

cycles. 

(r) New Pre-structural Modification 

Inspections and Structural Modification 

Before the accumulation of 20,800 total 

flight cycles: Do the applicable actions 

specified in paragraphs (r)(1) and (r)(2) of this 

AD. 

(1) Perform pre-structural modification 

inspections by doing the actions required by 

paragraphs (j), (n), and (o) of this AD. 

(2) Perform a structural modification of the 

aft pressure bulkhead by removing and 

replacing all stringer end fittings with new or 

refurbished fittings at stringers 1 through 14, 

and 52 through 64, in accordance with the 

Accomplishment Instructions of Lockheed 

Service Bulletin 093–53–105, Revision 3, 

dated May 31, 2013. 

(s) New Post-structural Modification 

Repetitive Inspections 

Within 13,875 flight cycles after 

performing the actions required by paragraph 

(r)(2) of this AD: Do the actions specified in 

paragraphs (j), (n), and (o) of this AD, and 

repeat thereafter at intervals not to exceed 

13,875 flight cycles. 

(t) No Reporting Requirement 

Although Lockheed Service Bulletin 093– 

53–105, Revision 3, dated May 31, 2013, 

referenced in this AD specifies to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

(u) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta 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 (v)(1) 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. 

(v) Related Information 

(1) For more information about this AD, 

contact Carl Gray, Aerospace Engineer, 

Airframe Branch, ACE–117A, FAA, Atlanta 

Aircraft Certification Office (ACO), 1701 

Columbia Avenue, College Park, GA 30337; 

phone: 404–474–5554; fax: 404–474–5605; 

email: carl.w.gray@faa.gov. 

(2) For service information identified in 

this AD, contact Lockheed Martin 

Corporation/Lockheed Martin Aeronautics 

Company, L1011 Technical Support Center, 

Dept. 6A4M, Zone 0579, 86 South Cobb 

Drive, Marietta, GA 30063–0579; telephone 

770–494–5444; fax 770–494–5445; email 

L1011.support@lmco.com; Internet http://

www.lockheedmartin.com/ams/tools/

TechPubs.html. 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 April 4, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–08302 Filed 4–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0195; Directorate 

Identifier 2013–NM–195–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 Directive (AD) 2008–17– 

03, which applies to certain The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes. 

AD 2008–17–03 currently requires 

repetitive inspections to detect fuselage 

frame cracking, and corrective action if 

necessary. AD 2008–17–03 also 

provides for optional terminating action 

(repair/preventive change) for the 

repetitive inspections. Since we issued 

AD 2008–17–03, we have determined 

that additional airplanes may be subject 

to the identified unsafe condition. This 

proposed AD would add airplanes to the 

applicability. For the newly added 

airplanes, however, this proposed AD 

would not provide terminating action 

for the repetitive inspections because 

service information has not been 

provided for a repair/preventive change. 

We are proposing this AD to detect and 

correct fuselage frame cracking, which 

could prevent the left forward entry 

door from sealing correctly, and could 

cause in-flight decompression of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by May 29, 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, 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. 

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–2014– 

0195; 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: 

Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

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

WA 98057–3356; phone: 425–917–6450; 

fax: 425–917–6590; email: alan.pohl@

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–2014–0195; Directorate Identifier 

2013–NM–195–AD’’ at the beginning of 

your comments. We specifically invite 

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Federal Register / Vol. 79, No. 71 / Monday, April 14, 2014 / Proposed Rules 20825 

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 August 6, 2008, we issued AD 

2008–17–03, Amendment 39–15641 (73 

FR 48288, August 19, 2008), for certain 

The Boeing Company Model 737–100, 

-200, -200C, -300, -400, and -500 series 

airplanes. AD 2008–17–03 required 

repetitive inspections to detect cracking 

of the body station 303.9 frame, and 

corrective action if necessary. AD 2008– 

17–03 also provided for optional 

terminating action for the repetitive 

inspections. AD 2008–17–03 resulted 

from reports of cracks found at the 

cutout in the web of body station frame 

303.9 inboard of stringer 16L. We issued 

AD 2008–17–03 to detect and correct 

such cracking, which could prevent the 

left forward entry door from sealing 

correctly, and could cause in-flight 

decompression of the airplane. 

Actions Since AD 2008–17–03, 

Amendment 39–15641 (73 FR 48288, 

August 19, 2008), Was Issued 

Since we issued AD 2008–17–03, 

Amendment 39–15641 (73 FR 48288, 

August 19, 2008), we have been advised 

that cracking has been discovered on an 

airplane outside the applicability of AD 

2008–17–03. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 737–53A1188, Revision 3, 

dated September 6, 2013. For 

information on the procedures and 

compliance times, see this service 

information at http://

www.regulations.gov by searching for 

Docket No. FAA–2014–0195. 

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 retain the 

requirements of AD 2008–17–03, 

Amendment 39–15641 (73 FR 48288, 

August 19, 2008). This proposed AD 

would add airplanes to the 

applicability. 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.’’ 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 

actions’’ correct or address any 

condition found. Corrective actions in 

an AD could include, for example, 

repairs. 

Differences Between the Proposed AD 

and the Service Information 

The service information 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 148 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS: REQUIRED ACTIONS

Action Labor cost Parts 

cost Cost per product Cost on U.S. operators 

Inspection ....... 31 to 33 work-hours × $85 per hour = up to $2,805 

per inspection cycle.

$0 Up to $2,805 per inspection 

cycle.

Up to $415,140 per inspection 

cycle. 

ESTIMATED COSTS: OPTIONAL MODIFICATION

Action Labor cost Parts cost Cost per 

product 

Repair/preventive change ........................ 12 to 30 work-hours × $85 per hour = up to $2,550 ............... $564 to $2,236 ....... Up to $4,786. 

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 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, 

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20826 Federal Register / Vol. 79, No. 71 / Monday, April 14, 2014 / Proposed Rules 

(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. Amend § 39.13 by removing 

Airworthiness Directive (AD) 2008–17– 

03, Amendment 39–15641 (73 FR 

48288, August 19, 2008), and adding the 

following new AD: 

The Boeing Company: Docket No. FAA– 

2014–0195; Directorate Identifier 2013– 

NM–195–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by May 29, 2014. 

(b) Affected ADs 

This AD supersedes AD 2008–17–03, 

Amendment 39–15641 (73 FR 48288, August 

19, 2008). 

(c) Applicability 

This AD applies to The Boeing Company 

airplanes, certificated in any category, 

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

this AD. 

(1) Model 737–100, -200, -200C, -300, -400, 

and -500 series airplanes, as identified in 

Boeing Alert Service Bulletin 737–53A1197, 

dated August 25, 2006. 

(2) Model 737–300, -400, and -500 series 

airplanes, as identified in Boeing Alert 

Service Bulletin 737–53A1188, Revision 3, 

dated September 6, 2013. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

found at the cutout in the web of body station 

frame 303.9 inboard of stringer 16L, and a 

new report of cracking found on an airplane 

not included in the applicability of AD 2008– 

17–03, Amendment 39–15641 (73 FR 48288, 

August 19, 2008). We are issuing this AD to 

detect and correct such cracking, which 

could prevent the left forward entry door 

from sealing correctly, and could cause inflight decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repetitive Inspections: Group 1 

Airplanes, Boeing Alert Service Bulletin 

737–53A1188, Revision 2, Dated May 9, 

2007, or Boeing Alert Service Bulletin 737– 

53A1188, Revision 3, Dated September 6, 

2013, With Revised Service Information 

This paragraph restates the requirements of 

paragraph (f) of AD 2008–17–03, Amendment 

39–15641 (73 FR 48288, August 19, 2008), 

with revised service information and airplane 

groupings. For airplanes identified as Group 

1 in Boeing Alert Service Bulletin 737– 

53A1188, Revision 3, dated September 6, 

2013: Do detailed and high frequency eddy 

current (HFEC) inspections in the web and 

doubler around the slotted holes in the frame 

web at stringers 15L and 16L, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1188, 

Revision 2, dated May 9, 2007; or Boeing 

Alert Service Bulletin 737–53A1188, 

Revision 3, dated September 6, 2013. Do the 

inspections at the applicable time specified 

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

Alert Service Bulletin 737–53A1188, 

Revision 3, dated September 6, 2013. Do all 

applicable corrective actions before further 

flight in accordance with Boeing Alert 

Service Bulletin 737–53A1188, Revision 2, 

dated May 9, 2007; or Boeing Alert Service 

Bulletin 737–53A1188, Revision 3, dated 

September 6, 2013; except as provided by 

paragraph (j)(3) of this AD. Repeat the 

inspections at intervals not to exceed 4,500 

flight cycles, until accomplishment of the 

repair/preventive change in accordance with 

Boeing Alert Service Bulletin 737–53A1188, 

Revision 2, dated May 9, 2007; or Boeing 

Alert Service Bulletin 737–53A1188, 

Revision 3, dated September 6, 2013; which 

terminates the repetitive inspection 

requirements for the airplanes identified in 

this paragraph. A repair/preventive change 

done using Boeing Alert Service Bulletin 

737–53A1188, dated April 9, 1998; or Boeing 

Alert Service Bulletin 737–53A1188, 

Revision 1, dated March 18, 1999; does not 

terminate the repetitive inspections, but the 

repetitive inspections may be terminated 

after the existing kit is replaced with a new 

kit in accordance with paragraph 3.B., Part II, 

step 3, or Part III, step 3, of Boeing Alert 

Service Bulletin 737–53A1188, Revision 2, 

dated May 9, 2007. As of the effective date 

of this AD, only Boeing Alert Service Bulletin 

737–53A1188, Revision 3, dated September 

6, 2013, may be used to do the actions 

required by this paragraph. 

Note 1 to paragraph (g) of this AD: 

Airplanes identified as Group 1 in Boeing 

Alert Service Bulletin 737–53A1188, 

Revision 3, dated September 6, 2013, are the 

same as those identified in Boeing Alert 

Service Bulletin 737–53A1188, Revision 2, 

dated May 9, 2007. 

(h) Retained Repetitive Inspections: Boeing 

Alert Service Bulletin 737–53A1197, Dated 

August 25, 2006 

This paragraph restates the requirements of 

paragraph (g) of AD 2008–17–03, 

Amendment 39–15641 (73 FR 48288, August 

19, 2008). For airplanes identified in Boeing 

Alert Service Bulletin 737–53A1197, dated 

August 25, 2006: Do an ultrasound 

inspection of the slot-shaped cutout in the 

web for the door stop strap at stringer 16L, 

an HFEC inspection of the web along the 

upper and lower edges of the doubler around 

the doorstop strap at stringer 16L, and a 

detailed inspection of the web around the 

doubler for the cutout at stringer 16L, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1197, dated August 25, 2006. Do the 

inspections at the applicable time specified 

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

Alert Service Bulletin 737–53A1197, dated 

August 25, 2006, except as provided by 

paragraph (j)(2) of this AD. Do all applicable 

corrective actions before further flight in 

accordance with Boeing Alert Service 

Bulletin 737–53A1197, dated August 25, 

2006, except as provided by paragraph (j)(3) 

of this AD. Repeat the inspections at intervals 

not to exceed 4,500 flight cycles, until 

accomplishment of the repair/preventive 

change in accordance with Boeing Alert 

Service Bulletin 737–53A1197, dated August 

25, 2006, which terminates the repetitive 

inspections. 

(i) New Repetitive Inspections: Group 2 

Airplanes, Boeing Alert Service Bulletin 

737–53A1188, Revision 3, Dated September 

6, 2013 

For airplanes identified as Group 2 in 

Boeing Alert Service Bulletin 737–53A1188, 

Revision 3, dated September 6, 2013: At the 

applicable times specified in Table 3 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–53A1188, 

Revision 3, dated September 6, 2013, except 

as required by paragraph (j)(1) of this AD: Do 

detailed and HFEC inspections for cracking 

in the web of the body station 303.9 frame 

at stringer 15L, and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1188, Revision 3, 

dated September 6, 2013, except as required 

by paragraph (j)(3) of this AD. Do all 

applicable corrective actions before further 

flight. Repeat the inspection thereafter at the 

applicable time specified in Table 3 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–53A1188, 

Revision 3, dated September 6, 2013. 

Accomplishment of a repair using a method 

approved in accordance with the procedures 

specified in paragraph (k) of this AD 

terminates the repetitive inspections required 

by this paragraph for the area covered by the 

repair. 

(j) Exceptions to Service Information 

Specifications 

(1) Where Boeing Alert Service Bulletin 

737–53A1188, Revision 3, dated September 

6, 2013, specifies a compliance time ‘‘after 

the Revision 3 date of this service bulletin,’’ 

this AD requires compliance within the 

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Federal Register / Vol. 79, No. 71 / Monday, April 14, 2014 / Proposed Rules 20827 

specified time after the effective date of this 

AD. 

(2) Where Boeing Alert Service Bulletin 

737–53A1197, dated August 25, 2006, 

specifies a compliance time ‘‘After the Date 

of this Service Bulletin,’’ this AD requires 

compliance for paragraph (h) of this AD 

within the specified time after September 23, 

2008 (the effective date of AD 2008–17–03, 

Amendment 39–15641 (73 FR 48288, August 

19, 2008)). For the initial inspection, the 

grace period for airplanes that have exceeded 

the specified threshold is extended to 4,500 

flight cycles after September 23, 2008 (the 

effective date of AD 2008–17–03). 

(3) Where Boeing Alert Service Bulletin 

737–53A1188, Revision 2, dated May 9, 2007; 

Boeing Alert Service Bulletin 737–53A1188, 

Revision 3, dated September 6, 2013; and 

Boeing Alert Service Bulletin 737–53A1197, 

dated August 25, 2006; specify to contact 

Boeing for appropriate action, including 

repair of damage outside the scope of the 

service information, repair using a method 

approved in accordance with the procedures 

specified in paragraph (k) of this AD. 

(k) 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 

paragraph (l)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-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, 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. 

(4) AMOCs approved for AD 2008–17–03, 

Amendment 39–15641 (73 FR 48288, August 

19, 2008), are approved as AMOCs for the 

corresponding provisions of this AD. 

(l) Related Information 

(1) For more information about this AD, 

contact Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6450; fax: 425–917–6590; 

email: alan.pohl@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 view 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 April 4, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–08301 Filed 4–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0226; Directorate 

Identifier 2014–CE–009–AD] 

RIN 2120–AA64 

Airworthiness Directives; Diamond 

Aircraft Industries GmbH Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for 

Diamond Aircraft Industries GmbH 

Models DA40 and DA40F airplanes that 

would supersede AD 2013–24–14, 

which resulted from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as the fatigue 

strength found in the aft main spar not 

ensuring unlimited lifetime structural 

integrity. We are issuing this proposed 

AD to require actions to address the 

unsafe condition on these products and 

to change the compliance time to 

coincide with other regulatory 

requirements. 

DATES: We must receive comments on 

this proposed AD by May 29, 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 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed AD, contact Diamond 

Aircraft Industries GmbH, N.A. OttoStr.5, A–2700 Wiener Neustadt, Austria; 

telephone: +43 2622 26700; fax: +43 

2622 26780; email: office@diamondair.at; Internet: http://

www.diamondaircraft.com/contact/

technical.php. You may review copies 

of the referenced service information at 

the FAA, Small Airplane Directorate, 

901 Locust, Kansas City, Missouri 

64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

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–2014– 

0226; 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 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Mike Kiesov, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4144; fax: (816) 

329–4090; email: mike.kiesov@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–2014–0226; Directorate Identifier 

2014–CE–009–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://

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. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS