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contains regulatory documents having general

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Rules and Regulations Federal Register

14805 

Vol. 80, No. 54 

Friday, March 20, 2015 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0749; Directorate 

Identifier 2014–NM–051–AD; Amendment 

39–18118; AD 2015–05–08] 

RIN 2120–AA64 

Airworthiness Directives; Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company Model 

382, 382B, 382E, 382F, and 382G 

airplanes. This AD was prompted by an 

evaluation by the design approval 

holder (DAH) indicating that the upper 

and lower rainbow fittings on the outer 

wing are subject to widespread fatigue 

damage (WFD). This AD requires 

repetitive inspections of the upper and 

lower rainbow fittings on the outer wing 

to detect cracks propagating from 

fasteners attaching the fittings to skin 

panels, and related investigative and 

corrective actions if necessary; and 

replacement of the upper and lower 

rainbow fittings on the outer wing. We 

are issuing this AD to prevent fatigue 

cracking of the upper and lower 

rainbow fittings on the outer wing and 

skin-panel-to-fitting fastener holes, 

which could result in reduced structural 

integrity of the airplane and possible 

separation of the wing from the 

airplane. 

DATES: This AD is effective April 24, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 24, 2015. 

ADDRESSES: For service information 

identified in this 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. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2014–0749. 

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– 

0749; 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

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– 

474–5606; email: Carl.W.Gray@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Lockheed Martin 

Corporation/Lockheed Martin 

Aeronautics Company Model 382, 382B, 

382E, 382F, and 382G airplanes. The 

NPRM published in the Federal 

Register on October 16, 2014 (79 FR 

62075). The NPRM was prompted by an 

evaluation by the DAH indicating that 

the upper and lower rainbow fittings on 

the outer wing are subject to WFD. The 

NPRM proposed to require repetitive 

inspections of the upper and lower 

rainbow fittings on the outer wing to 

detect cracks propagating from fasteners 

attaching the fittings to skin panels, and 

related investigative and corrective 

actions if necessary; and replacement of 

the upper and lower rainbow fittings on 

the outer wing. We are issuing this AD 

to prevent fatigue cracking of the upper 

and lower rainbow fittings on the outer 

wing and skin-panel-to-fitting fastener 

holes, which could result in reduced 

structural integrity of the airplane and 

possible separation of the wing from the 

airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

The commenter supported the NPRM 

(79 FR 62075, October 16, 2014). 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

62075, October 16, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 62075, 

October 16, 2014). 

Related Service Information Under 1 

CFR Part 51 

We reviewed Lockheed Martin 

Aeronautics Company Service Bulletin 

382–57–95, including Appendix A, 

dated December 16, 2013. The service 

bulletin describes procedures for 

inspection and replacement of the upper 

and lower rainbow fittings on the outer 

wing, and corrective actions. This 

service information is reasonably 

available; see ADDRESSES for ways to 

access this service information. 

Costs of Compliance 

We estimate that this AD affects 20 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

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14806 Federal Register / Vol. 80, No. 54 / Friday, March 20, 2015 / Rules and Regulations 

ESTIMATED COSTS

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

ECSS inspection .................... 24 work-hours × $85 per hour 

= $2,040 per inspection 

cycle.

$0 $2,040 per inspection cycle ... $40,800 per inspection cycle. 

Bolt hole inspection during 

rainbow fitting replacement.

24 work-hours × $85 per hour 

= $2,040.

0 2,040 ...................................... 40,800. 

Replacement of all four rainbow fittings.2,060 work-hours × $85 per 

hour = $175,100.

28,000 203,100 .................................. 4,062,000. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement of one rainbow fitting .............................. 515 work-hours × $85 per hour = $43,775 .................. $7,000 $50,775 

We have received no definitive data 

that would enable us to provide cost 

estimates for on-condition actions for 

cracking of the skin-panel-to-fitting 

fastener holes specified in this 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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will 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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2015–05–08 Lockheed Martin Corporation/ 

Lockheed Martin Aeronautics Company: 

Amendment 39–18118 ; Docket No. 

FAA–2014–0749; Directorate Identifier 

2014–NM–051–AD. 

(a) Effective Date 

This AD is effective April 24, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Lockheed Martin 

Corporation/Lockheed Martin Aeronautics 

Company Model 382, 382B, 382E, 382F, and 

382G airplanes; certificated in any category; 

having any outer wing serial number 4542 

and subsequent, or any manufacturing end 

product (MEP) replacement outer wing 

except 14Y series. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder (DAH) indicating 

that the upper and lower rainbow fittings on 

the outer wing are subject to widespread 

fatigue damage (WFD). We are issuing this 

AD to prevent fatigue cracking of the upper 

and lower rainbow fittings on the outer wing 

and skin-panel-to-fitting fastener holes, 

which could result in reduced structural 

integrity of the airplane and possible 

separation of the wing from the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Eddy Current Surface Scan 

(ECSS) Inspections 

At the later of the times specified in 

paragraphs (g)(1) and (g)(2) of this AD: Do an 

ECSS inspection of the left and right outer 

wing upper and lower rainbow fitting-toskin-panel attachments to detect cracks 

propagating from fasteners attaching the 

fittings to skin panels, and do all applicable 

related investigative actions, in accordance 

with the Accomplishment Instructions of 

Lockheed Martin Aeronautics Company 

Service Bulletin 382–57–95, including 

Appendix A, dated December 16, 2013, 

except as provided by paragraph (j)(1) of this 

AD. Do all applicable related investigative 

actions before further flight. If any cracking 

is found during any inspection required by 

this paragraph, before further flight, repair 

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Federal Register / Vol. 80, No. 54 / Friday, March 20, 2015 / Rules and Regulations 14807 

the cracking, using a method approved in 

accordance with the procedures specified in 

paragraph (m) of this AD. Repeat the 

inspection of the left and right outer wing 

upper and lower rainbow fitting-to-skinpanel attachments thereafter at intervals not 

to exceed 2,000 flight hours, except as 

provided by paragraph (l) of this AD. 

(1) Before the accumulation of 30,000 total 

flight hours on any wing. 

(2) Within 365 days or 600 flight hours, 

whichever occurs first, after the effective date 

of this AD. 

(h) Rainbow Fitting Replacement and 

Inspections 

At the time specified in paragraph (i) of 

this AD, do the actions required by paragraph 

(h)(1) and (h)(2) of this AD. 

(1) Do a detailed inspection of the wing 

faying structure for damage and cracks, and 

do an automated bolt hole eddy current 

inspection on all open fastener holes in the 

mating structure, stiffeners, webs and angles 

for cracking, in accordance with the 

Accomplishment Instructions of Lockheed 

Martin Aeronautics Company Service 

Bulletin 382–57–95, including Appendix A, 

dated December 16, 2013, except as provided 

by paragraph (j)(1) of this AD. 

(i) If any damage is found during any 

inspection required by paragraph (h)(1) of 

this AD, before further flight, repair the 

damage, using a method approved in 

accordance with the procedures specified in 

paragraph (m) of this AD. 

(ii) If any cracking is found during any 

inspection required by paragraph (h)(1) of 

this AD, before further flight, repair the 

cracking, in accordance with the 

Accomplishment Instructions of Lockheed 

Martin Aeronautics Company Service 

Bulletin 382–57–95, including Appendix A, 

dated December 16, 2013, except as provided 

by paragraphs (j)(1) and (j)(2) of this AD. 

(2) Replace the left and right upper and 

lower rainbow fittings of the outer wing with 

new fittings, in accordance with the 

Accomplishment Instructions of Lockheed 

Martin Aeronautics Company Service 

Bulletin 382–57–95, including Appendix A, 

dated December 16, 2013. 

Note 1 to paragraph (h) of this AD: AD 

2012–06–09, Amendment 39–16990 (77 FR 

21404, April 10, 2012), is related to the 

rainbow fitting replacement. AD 2012–06–09 

references the Lockheed Martin Model 382, 

382B, 382E, 382F, and 382G Series Aircraft 

Service Manual Publication (SMP), 

Supplemental Structural Inspection 

Document (SSID), SMP 515–C–SSID, Change 

1, dated September 10, 2010; which contains 

inspections for the entire Model 382B–H 

airframe, not just the outer wing. Since 

installing new rainbow fittings, as required 

by paragraph (g) of this AD, resets the 

accumulated service life on certain parts to 

zero, certain compliance times specified in 

Table 3 of this SSID would be affected by the 

installation of new outer wing fittings. 

Note 2 to paragraph (h) of this AD: AD 

2011–15–02, Amendment 39–16749 (76 FR 

41647, July 15, 2011), has requirements for 

fuel system limitations and critical design 

configuration control limitations, which 

might include configuration or parts 

limitations on areas affected by 

accomplishment of this AD. 

(i) Compliance Times for Paragraph (h) of 

This AD 

At the later of the times specified in 

paragraph (i)(1) and (i)(2) of this AD, do the 

actions required by paragraph (h) of this AD. 

(1) Before the accumulation of 50,000 total 

flight hours on any wing. 

(2) Within 60 days or 100 flight hours, 

whichever occurs first, after the effective date 

of this AD. 

(j) Exceptions to Service Information 

Specifications 

(1) Although Lockheed Martin Aeronautics 

Company Service Bulletin 382–57–95, 

including Appendix A, dated December 16, 

2013, specifies to submit certain information 

to the manufacturer, this AD does not 

include that requirement. 

(2) Where Lockheed Martin Aeronautics 

Company Service Bulletin 382–57–95, 

including Appendix A, dated December 16, 

2013, specifies to contact Lockheed for repair 

instructions, before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (m) of 

this AD. 

(k) Parts Installation Limitation 

After replacement of the left and right 

upper and lower rainbow fittings of the outer 

wing with new fittings, as required by 

paragraph (h) of this AD, any subsequent 

rainbow fitting replacements must be done 

using a method approved in accordance with 

the procedures specified in paragraph (m) of 

this AD. 

(l) Outer Wing Flight Hours Adjustment 

For any wing on which the left or right 

upper and lower rainbow fittings of the outer 

wing have been replaced with new fittings as 

required by paragraph (h) of this AD: Before 

the accumulation of 30,000 flight hours after 

accomplishing the replacement, do the 

inspection required by paragraph (g) of this 

AD and repeat thereafter at the times 

specified in paragraph (g) of this AD. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta 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 (n) 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 a 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company Designated 

Engineering Representative (DER) that has 

been authorized by the Manager, Atlanta 

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. 

(n) Related Information 

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: 404–474–5606; 

email: Carl.W.Gray@faa.gov. 

(o) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Lockheed Martin Aeronautics Company 

Service Bulletin 382–57–95, including 

Appendix A, dated December 16, 2013. 

(ii) Reserved. 

(3) For Lockheed service information 

identified in this 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. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on March 6, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–05789 Filed 3–19–15; 8:45 am] 

BILLING CODE 4910–13–P 

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