32066 Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 

March 17, 1997: At the later of the times 

specified by paragraphs (h)(3)(i) and (h)(3)(ii) 

of this AD: 

(i) Within 24,900 flight cycles or 49,800 

flight hours, whichever occurs first, since the 

modification specified in Airbus Service 

Bulletin A320–57–1017, dated September 3, 

1991; or Airbus Service Bulletin A320–57– 

1017, Revision 01, dated March 17, 1997, was 

accomplished. 

(ii) Within 850 flight cycles or 1,700 flight 

hours, whichever occurs first, after the 

effective date of this AD. 

(4) For Configuration 4 airplanes, having 

MSN 0080 to 0155 inclusive: 

At the later of the times specified in 

paragraphs (h)(4)(i) or (h)(4)(ii) of this AD: 

(i) Before exceeding 54,300 flight cycles or 

108,600 flight hours, whichever occurs first 

since airplane first flight. 

(ii) Within 60 days after the effective date 

of this AD. 

(i) Repair 

If any crack is detected during any 

inspection required by paragraph (g) of this 

AD: Before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA). 

(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, 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: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0069, dated 

March 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– 

2015–1422. 

(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 May 18, 

2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–13342 Filed 6–4–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1421; Directorate 

Identifier 2014–NM–177–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 767–300 

and –300F series airplanes. This 

proposed AD was prompted by reports 

of fatigue cracking on airplanes with 

Aviation Partners Boeing winglets 

installed. This proposed AD would 

require a high frequency eddy current 

(HFEC) inspection for cracking of the 

lower outboard wing skin, and repair or 

modification if necessary. This 

proposed AD would also require one of 

three follow-on actions: Repeating the 

HFEC inspections; modifying certain 

internal stringers and oversizing and 

plugging the existing fastener holes of 

the lower wing; or modifying the 

external doubler/tripler and doing 

repetitive post-modification inspections. 

We are proposing this AD to prevent 

fatigue cracking in the lower outboard 

wing skin, which could result in failure 

and subsequent separation of the wing 

and winglet and consequent reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by July 20, 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 Aviation 

Partners Boeing, 2811 S. 102nd Street, 

Suite 200, Seattle, WA 98168; telephone 

206–762–1171; Internet https://

www.aviationpartnersboeing.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– 

1421; 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: 

Allen Rauschendorfer, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6487; 

fax: 425–917–6590; email: 

Allen.Rauschendorfer@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– 

2015–1421; Directorate Identifier 2014– 

NM–177–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 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 32067 

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 have received reports of fatigue 

cracking in the lower outboard wing 

skin at the inboard fastener of stringer 

L–9.5 on Model 767–300 airplanes with 

Aviation Partners Boeing winglets 

installed. The cracks were found at the 

fastener holes common to the inboard 

end of the outboard stringer L–9.5 on 

the left- and right-hand wings. 

Investigation revealed that these were 

fatigue cracks related to Aviation 

Partners Boeing STC ST01920SE 

winglet retrofit kit installations. If not 

corrected, these cracks could extend to 

adjacent structure and could lead to 

reduced load carrying capability in the 

lower skin. Later investigation revealed 

more cracking along the lower wing skin 

as a result of fatigue due to higher-thanpredicted fastener loads and skin stress 

peaking at the inboard end of stringer L– 

9.5. These conditions, if not corrected, 

could result in failure and subsequent 

separation of the wing and winglet, and 

consequent reduced controllability of 

the airplane. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Aviation Partners 

Boeing Service Bulletin AP767–57–010, 

Revision 7, dated November 4, 2014. 

The service information describes 

procedures for inspecting for cracking of 

the external surface of the lower 

outboard wing skin, and repair or 

modification if necessary. The service 

information also includes certain 

follow-on actions. 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 

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 

‘‘Difference Between this Proposed Rule 

and the Service Information.’’ 

Difference Between Proposed Rule and 

Service Information 

Aviation Partners Boeing Service 

Bulletin AP767–57–010, Revision 7, 

dated November 4, 2014, 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 140 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 ............................... 3 work-hours × $85 per hour = $255 ..................................... $0 $255 $35,700 

ESTIMATED COSTS—OPTIONAL ACTIONS

Action Labor cost Parts cost Cost per 

product 

Repetitive inspections ...................... 3 work-hours × $85 per hour = $255 per inspection cycle ....................... $0 $255 

Repair/Modification .......................... 262 work-hours × $85 per hour = $22,270 ............................................... 0 22,270 

Terminating Modification .................. 262 work-hours × $85 per hour = $22,270 ............................................... 0 22,270 

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 


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32068 Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 

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– 

2015–1421; Directorate Identifier 2014– 

NM–177–AD. 

(a) Comments Due Date 

We must receive comments by July 20, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 767–300 and –300F series airplanes, 

certificated in any category, with Aviation 

Partners Boeing winglets installed; as 

identified in Aviation Partners Boeing 

Service Bulletin AP767–57–010, Revision 7, 

dated November 4, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fatigue cracking in the lower outboard wing 

skin at the inboard fastener of stringer L–9.5 

on airplanes with winglets installed per 

Supplemental Type Certificate ST01920SE. 

We are issuing this AD to prevent fatigue 

cracking in the lower outboard wing skin, 

which could result in failure and subsequent 

separation of the wing and winglet and 

consequent reduced controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Repair or Modification 

and Post-Repair or Modification Inspections 

At the applicable time specified in 

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

Partners Boeing Service Bulletin AP767–57– 

010, Revision 7, dated November 4, 2014, 

except as required by paragraph (j) of this 

AD: Do a high frequency eddy current 

(HFEC) inspection for cracking of the lower 

outboard wing skin, as specified in paragraph 

(g)(1) or (g)(2) of this AD, as applicable. 

(1) For Groups 1 and 2 airplanes: Do an 

internal HFEC inspection at the inboard 

fasteners of stringer L–9.5, in accordance 

with PART 1 of the Accomplishment 

Instructions of Aviation Partners Boeing 

Service Bulletin AP767–57–010, Revision 7, 

dated November 4, 2014; and do the 

applicable actions required by paragraph 

(g)(1)(i) or (g)(1)(ii) of this AD. 

(i) If any cracking is found, before further 

flight, do the repair or modification specified 

in paragraph (h) of this AD. 

(ii) If no cracking is found, do the 

applicable actions specified in paragraph 

(g)(1)(ii)(A), (g)(1)(ii)(B), or (g)(1)(ii)(C) of this 

AD at the time specified in paragraph 1.E., 

‘‘Compliance,’’ of Aviation Partners Boeing 

Service Bulletin AP767–57–010, Revision 7, 

dated November 4, 2014. 

(A) Repeat the HFEC inspection. 

(B) Do a preventive modification of the 

external doubler/tripler filler and stringer L– 

6.5, in accordance with PART 2 through 6, 

or PART 8, as applicable, of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

010, Revision 7, dated November 4, 2014. If 

PART 8 was done, do repetitive HFEC 

inspections for cracking of the lower 

outboard wing skin common to the external 

doubler/tripler repair, in accordance with 

PART 9 of the Accomplishment Instructions 

of Aviation Partners Boeing Service Bulletin 

AP767–57–010, Revision 7, dated November 

4, 2014, except as required by paragraph (j)(2) 

of this AD. If any cracking is found: Before 

further flight, do a repair or modification 

using a method approved in accordance with 

the procedures specified in paragraph (k) of 

this AD. 

(C) Do a repair or modification in 

accordance with PART 8, and do repetitive 

HFEC inspections for cracking of the lower 

outboard wing skin common to the external 

doubler/tripler repair, in accordance with 

PART 9 of the Accomplishment Instructions 

of Aviation Partners Boeing Service Bulletin 

AP767–57–010, Revision 7, dated November 

4, 2014, except as required by paragraph (j)(2) 

of this AD. If any cracking is found: Before 

further flight, do a repair or modification 

using a method approved in accordance with 

the procedures specified in paragraph (k) of 

this AD. 

(2) For Group 3 airplanes: Do an internal 

HFEC inspection at the inboard fasteners of 

stringer L–9.5, in accordance with PART 7a 

of the Accomplishment Instructions of 

Aviation Partners Boeing Service Bulletin 

AP767–57–010, Revision 7, dated November 

4, 2014. Do an external HFEC inspection at 

the inboard fasteners of stringer L–6.5 in 

accordance with PART 7b of the 

Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

010, Revision 7, dated November 4, 2014; 

and do the applicable actions required by 

paragraph (g)(2)(i) or (g)(2)(ii) of this AD, at 

the time specified in paragraph 1.E., 

‘‘Compliance,’’ of Aviation Partners Boeing 

Service Bulletin AP767–57–010, Revision 7, 

dated November 4, 2014. 

(i) If any cracking is found: Before further 

flight, do a repair or modification using a 

method approved in accordance with the 

procedures specified in paragraph (k) of this 

AD. 

(ii) If no cracking is found: Repeat the 

HFEC inspections at the time specified in 

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

Partners Boeing Service Bulletin AP767–57– 

010, Revision 7, dated November 4, 2014. 

(h) Terminating Modification and Repair 

and Post-Repair or Modification Inspections 

Modification of the external doubler/tripler 

filler and stringer L–6.5, in accordance with 

PART 2 through PART 6, or repair or 

modification in accordance with PART 8, of 

the Accomplishment Instructions of Aviation 

Partners Boeing Service Bulletin AP767–57– 

010, Revision 7, dated November 4, 2014, 

except as required by paragraph (j)(2) of this 

AD, terminates the repetitive inspections 

specified in paragraph (g)(1)(ii)(A) of this AD, 

provided the conditions specified in 

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

met. If any cracking is found: Before further 

flight, do a repair or modification using a 

method approved in accordance with the 

procedures specified in paragraph (k) of this 

AD. 

(1) The repair or modification must be 

done within the applicable time specified in 

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

Partners Boeing Service Bulletin AP767–57– 

010, Revision 7, dated November 4, 2014, 

except as required by paragraph (j) of this 

AD. 

(2) Repetitive post-repair or modification 

inspections for cracking of the lower 

outboard wing skin common to the external 

doubler/tripler repair must be done in 

accordance with PART 9 of Aviation Partners 

Boeing Service Bulletin AP767–57–010, 

Revision 7, dated November 4, 2014, within 

the applicable time specified in paragraph 

1.E., ‘‘Compliance,’’ of Aviation Partners 

Boeing Service Bulletin AP767–57–010, 

Revision 7, dated November 4, 2014, except 

as required by paragraph (j)(2) of this AD. If 

any cracking is found: Before further flight, 

do a repair or modification using a method 

approved in accordance with the procedures 

specified in paragraph (k) of this AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraphs (g) and (h) of 

this AD, if those actions were performed 

before the effective date of this AD using the 

service information identified in paragraph 

(i)(1), (i)(2), or (i)(3) of this AD; which is not 

incorporated by reference in this AD. 

(1) Aviation Partners Boeing Service 

Bulletin AP767–57–010, Revision 2, dated 

January 23, 2014. 

(2) Aviation Partners Boeing Service 

Bulletin AP767–57–010, Revision 4, dated 

April 22, 2014. 

(3) Aviation Partners Boeing Service 

Bulletin AP767–57–010, Revision 6, dated 

August 15, 2014. 

(j) Exceptions to Service Information 

Specifications 

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

Aviation Partners Boeing Service Bulletin 

AP767–57–010, Revision 7, dated November 


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4, 2014, specifies a compliance time ‘‘after 

the initial issue date on this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) Where Aviation Partners Boeing Service 

Bulletin AP767–57–010, Revision 7, dated 

November 4, 2014, specifies to contact 

Boeing for repair instructions: Before further 

flight, repair the cracking 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. 

(l) Related Information 

(1) For more information about this AD, 

contact Allen Rauschendorfer, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6487; fax: 425–917– 

6590; email: Allen.Rauschendorfer@faa.gov. 

(2) For service information identified in 

this AD, contact Aviation Partners Boeing, 

2811 S. 102nd Street, Suite 200, Seattle, WA 

98168; telephone 206–762–1171; Internet 

https://www.aviationpartnersboeing.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 May 13, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–13328 Filed 6–4–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1419; Directorate 

Identifier 2014–NM–183–AD] 

RIN 2120–AA64 

Airworthiness Directives; Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics 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 all 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company Model 

188 series airplanes. This proposed AD 

was prompted by an evaluation by the 

design approval holder (DAH) 

indicating the left and right lower 

surface panels of the wings are subject 

to widespread fatigue damage (WFD). 

This proposed AD would require 

repetitive inspections for cracking at 

these panels, and repair if necessary. 

The proposed AD would also require a 

one-time bolt-hole eddy current 

inspection of all open holes for 

cracking, repair if necessary, and 

modification. We are proposing this AD 

to prevent fatigue cracking of the left 

and right lower surface panels of the 

wings, which could result in reduced 

structural integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by July 20, 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 Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company, Airworthiness 

Office, Dept. 6A0M, Zone 0252, Column 

P–58, 86 S. Cobb Drive, Marietta, GA 

30063; telephone 770–494–5444; fax 

770–494–5445; email ams.portal@

lmco.com; Internet http://

www.lockheedmartin.com/ams/tools/

TechPubs.html. 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– 

1419; 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: 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. 

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– 

2015–1419; Directorate Identifier 2014– 

NM–183–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 

Structural fatigue damage is 

progressive. It begins as minute cracks, 

and those cracks grow under the action 

of repeated stresses. This can happen 

because of normal operational 

conditions and design attributes, or 

because of isolated situations or 

incidents such as material defects, poor 

fabrication quality, or corrosion pits, 


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