Federal Register / Vol. 80, No. 68 / Thursday, April 9, 2015 / Rules and Regulations 19013 

(i) Repair 

(1) If any disbonding is confirmed during 

any inspection required by paragraphs 

(h)(1)(i) and (h)(1)(ii) of this AD, before 

further flight, repair as specified in 

paragraphs (i)(1)(i) and (i)(1)(ii) of this AD, as 

applicable. 

(i) If disbonding is less than or equal to 50 

millimeters (mm) in width and less than or 

equal to 150 mm in length, before further 

flight, vent the core, using a method 

approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA. Within 100 flight cycles 

after the UT inspection specified in 

paragraph (h) of this AD is done, repair using 

a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA. 

(ii) If disbonding is greater than 50 mm in 

width or greater than 150 mm in length, 

before further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or EASA; or Airbus’s EASA 

DOA. 

(2) If liquid ingress is confirmed during 

any inspection required by paragraphs 

(h)(1)(i) and (h)(1)(ii) of this AD, before 

further flight, repair using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or EASA; or Airbus’s EASA 

DOA. 

(j) Inspection after Re-Installation 

If any rudder has been inspected as 

specified in Airbus Service Bulletin A300– 

55–6043, Revision 01, dated December 3, 

2007; or A310–55–2044, Revision 01, dated 

December 3, 2007; as applicable; and has 

been removed and re-installed on any 

airplane after this inspection, that rudder 

must be re-inspected as required by 

paragraph (g) of this AD; and all applicable 

actions required by paragraphs (h) and (i) of 

this AD must be done. 

(k) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install, on any airplane, a rudder 

assembly having a part number starting with 

A55471500, unless it has been inspected as 

required by paragraph (h) of this AD, and all 

applicable actions required by paragraph (i) 

of this AD have been done. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; 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: 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 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(m) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0039, dated 

February 26, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0123-0002. 

(n) 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 this AD specifies otherwise. 

(i) Airbus Alert Operators Transmission 

(AOT) A55W002–12, dated December 13, 

2012, including Inspection Flowchart. The 

inspection flowchart attached to this AOT is 

referred to in the AOT as ‘‘Appendix 1’’; 

however, the flowchart page does not 

identify itself as an appendix. While the 

inspection flowchart page does specify the 

AOT document number, it does not specify 

a revision level or an issue date. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 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. 

(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 

27, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–07799 Filed 4–8–15; 08:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0627; Directorate 

Identifier 2013–NM–217–AD; Amendment 

39–18126; AD 2015–06–08] 

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 superseding 

Airworthiness Directive (AD) 2011–09– 

03 for all Lockheed Martin Corporation/ 

Lockheed Martin Aeronautics Company 

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

airplanes. AD 2011–09–03 required 

repetitive eddy current inspections to 

detect cracks in the center wing upper 

and lower rainbow fittings, and 

corrective actions if necessary; and 

repetitive replacement of rainbow 

fittings, which would extend the 

repetitive interval for the next 

inspection. This new AD requires 

reduced intervals for inspections of the 

upper rainbow fittings. This AD was 

prompted by analysis of in-service 

cracking, which has shown that a 

reduction in the inspection intervals is 

necessary for the upper rainbow fittings. 

We are issuing this AD to detect and 

correct fatigue cracking of the upper and 

lower rainbow fittings on the center 

wings, which could grow large and lead 

to the failure of the fitting and a 

catastrophic failure of the center wing. 

DATES: This AD is effective May 14, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 14, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of May 26, 2011 (76 FR 

22311, April 21, 2011). 

ADDRESSES: For service information 

identified in this AD, contact Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company, Airworthiness 


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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–2014–0627. 

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– 

0627; 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 to supersede AD 2011–09–03, 

Amendment 39–16665 (76 FR 22311, 

April 21, 2011). AD 2011–09–03 applied 

to all Lockheed Martin Corporation/

Lockheed Martin Aeronautics Company 

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

airplanes. The NPRM published in the 

Federal Register on September 17, 2014 

(79 FR 55675). The NPRM was 

prompted by analysis of in-service 

cracking, which has shown that the 

initial and repetitive inspection 

schedules for the upper rainbow fitting 

need to be revised to reduce the 

probability of failure until the rainbow 

fitting is replaced. The NPRM proposed 

to continue to require repetitive eddy 

current inspections to detect cracks in 

the center wing upper and lower 

rainbow fittings, and corrective actions 

if necessary; and repetitive replacement 

of rainbow fittings, which would extend 

the repetitive interval for the next 

inspection. This AD reduces compliance 

times for initial and repetitive 

inspections of the upper rainbow fitting. 

We are issuing this AD to detect and 

correct fatigue cracking of the upper and 

lower rainbow fittings on the center 

wings, which could grow large and lead 

to the failure of the fitting and a 

catastrophic failure of the center wing. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 55675, September 17, 2014) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data 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 

55675, September 17, 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 55675, 

September 17, 2014). 

Related Service Information Under 1 

CFR Part 51 

We reviewed Lockheed Martin 

Aeronautics Company Service Bulletin 

382–57–82, Revision 6, including 

Appendixes A, B, and C, dated July 11, 

2013. The service information describes 

procedures for repetitive eddy current 

inspections of the upper and lower 

rainbow fittings of the center wing; 

repetitive replacement of the upper and 

lower rainbow fittings; and related 

investigative 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 14 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection of upper and lower fitting [retained actions from 

AD 2011-09-03, Amendment 39-16665 (76 FR 22311, 

April 21, 2011)].

20 work-hours × $85 per hour 

= $1,700 per inspection 

cycle.

None .............. $1,700, per inspection 

cycle.

$23,800, per 

inspection 

cycle. 

Fitting replacement [retained actions from AD 2011-09-03, 

Amendment 39-16665 (76 FR 22311, April 21, 2011)].

2,438 work-hours × $85 per 

hour = $207,230 per replacement.

$40,000 .......... $247,230, per 

replacement.

$3,461,220, 

per replacement. 

This AD reduces the compliance 

times for the upper rainbow fitting 

inspections and adds no additional 

economic burden. 

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 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, 


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Federal Register / Vol. 80, No. 68 / Thursday, April 9, 2015 / Rules and Regulations 19015 

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 

removing Airworthiness Directive (AD) 

2011–09–03, Amendment 39–16665 (76 

FR 22311, April 21, 2011), and adding 

the following new AD: 

2015–06–08 Lockheed Martin Corporation/ 

Lockheed Martin Aeronautics Company: 

Amendment 39–18126; Docket No. 

FAA–2014–0627; Directorate Identifier 

2013–NM–217–AD. 

(a) Effective Date 

This AD is effective May 14, 2015. 

(b) Affected ADs 

This AD replaces AD 2011–09–03, 

Amendment 39–16665 (76 FR 22311, April 

21, 2011). 

(c) Applicability 

This AD applies to all Lockheed Martin 

Corporation/Lockheed Martin Aeronautics 

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

382G airplanes, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by an analysis of 

in-service cracking that has shown that the 

rainbow fittings are susceptible to multiple 

site fatigue damage. We are issuing this AD 

to detect and correct fatigue cracking of the 

upper and lower rainbow fittings on the 

center wings, which could grow large and 

lead to the failure of the fitting and a 

catastrophic failure of the center wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Initial Inspections 

This paragraph restates the requirements of 

paragraph (g) of AD 2011–09–03, 

Amendment 39–16665 (76 FR 22311, April 

21, 2011), with revised service information. 

Except as required by paragraph (m) of this 

AD, at the later of the times specified in 

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

eddy current inspections to detect cracking of 

the center wing upper and lower rainbow 

fittings on the left and right side of the 

airplane. Do the actions in accordance with 

the Accomplishment Instructions of 

Lockheed Service Bulletin 382–57–82, 

Revision 4, including Appendixes A and B, 

dated May 20, 2009; or Lockheed Martin 

Aeronautics Company Service Bulletin 382– 

57–82, Revision 6, including Appendixes A 

and B, dated July 11, 2013. If any crack is 

found during the inspections required by this 

paragraph, before further flight, do the 

actions required by paragraph (k) of this AD. 

Doing the requirements of paragraph (m) of 

this AD terminates the requirements of this 

paragraph for the affected upper rainbow 

fitting only. As of the effective date of this 

AD, only use Lockheed Martin Aeronautics 

Company Service Bulletin 382–57–82, 

Revision 6, including Appendixes A and B, 

dated July 11, 2013, for accomplishing the 

actions specified in this paragraph. 

(1) Before the accumulation of 15,000 total 

flight hours on the rainbow fitting. 

(2) Within 365 days or 600 flight hours on 

the rainbow fitting after May 26, 2011, (the 

effective date of AD 2011–09–03, 

Amendment 39–16665 (76 FR 22311, April 

21, 2011)), whichever occurs first. 

(h) Retained Repetitive Inspection Schedule 

This paragraph restates the requirements of 

paragraph (h) of AD 2011–09–03, 

Amendment 39–16665 (76 FR 22311, April 

21, 2011), with a new exception. Except as 

required by paragraph (n) of this AD, repeat 

the inspection required by paragraph (g) of 

this AD at intervals not to exceed 3,600 flight 

hours on the center wing, until the rainbow 

fitting has accumulated 30,000 total flight 

hours. If any crack is found during the 

inspections required by this paragraph, 

before further flight, do the actions required 

by paragraph (k) of this AD. Doing the 

requirements of paragraph (n) of this AD 

terminates the requirements of this paragraph 

for the affected upper rainbow fitting only. 

(i) Retained Rainbow Fitting Replacements 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–09–03, Amendment 

39–16665 (76 FR 22311, April 21, 2011), with 

revised service information. Before the 

accumulation of 30,000 flight hours on the 

rainbow fitting, or within 600 flight hours 

after May 26, 2011, (the effective date of AD 

2011–09–03, Amendment 39–16665 (76 FR 

22311, April 21, 2011)), whichever occurs 

later: Replace the rainbow fitting with a new 

rainbow fitting, do all related investigative 

actions, and do all applicable corrective 

actions, in accordance with paragraph 2.C. of 

the Accomplishment Instructions of 

Lockheed Service Bulletin 382–57–82, 

Revision 4, including Appendix C, dated 

May 20, 2009, except as required by 

paragraph (l) of this AD; or Lockheed Martin 

Aeronautics Company Service Bulletin 382– 

57–82, Revision 6, including Appendix C, 

dated July 11, 2013, except as required by 

paragraph (l) of this AD. Replace the rainbow 

fitting thereafter at intervals not to exceed 

30,000 flight hours. As of the effective date 

of this AD, only use Lockheed Martin 

Aeronautics Company Service Bulletin 382– 

57–82, Revision 6, including Appendix C, 

dated July 11, 2013, for accomplishing the 

actions specified in this paragraph. 

(j) Retained Post-Replacement Repetitive 

Inspections 

This paragraph restates the requirements of 

paragraph (j) of AD 2011–09–03, Amendment 

39–16665 (76 FR 22311, April 21, 2011), with 

a new exception. For upper and lower 

rainbow fittings replaced in accordance with 

paragraph (i) or (k) of this AD: Except as 

required by paragraph (o) of this AD, do the 

eddy current inspections specified in 

paragraph (g) of this AD within 15,000 flight 

hours after doing the replacement and repeat 

the eddy current inspections specified in 

paragraph (h) of this AD thereafter at 

intervals not to exceed 3,600 flight hours 

until the rainbow fittings are replaced in 

accordance with paragraph (i) or (k) of this 

AD. Doing the requirements of paragraph (o) 

of this AD terminates the requirements of this 

paragraph for the affected upper rainbow 

fitting only. 

(k) Retained Replacement, Related 

Investigative Actions, and Corrective 

Actions 

This paragraph restates the requirements of 

paragraph (k) of AD 2011–09–03, 

Amendment 39–16665 (76 FR 22311, April 

21, 2011), with revised service information 

and revised references to inspection 

paragraphs. If, during any inspection 

required by paragraph (g), (h), (m), or (n) of 

this AD, any crack is detected in the rainbow 

fitting, before further flight, replace the 

rainbow fitting with a new rainbow fitting, 

do all related investigative actions, and do all 

applicable corrective actions, in accordance 

with Paragraph 2.C. of the Accomplishment 

Instructions of Lockheed Service Bulletin 

382–57–82, Revision 4, including Appendix 

C, dated May 20, 2009, except as provided by 

paragraph (l) of this AD; or Lockheed Martin 

Aeronautics Company Service Bulletin 382– 

57–82, Revision 6, including Appendix C, 

dated July 11, 2013, except as required by 

paragraph (l) of this AD. As of the effective 

date of this AD, only use Lockheed Martin 

Aeronautics Company Service Bulletin 382– 

57–82, Revision 6, including Appendix C, 

dated July 11, 2013, for accomplishing the 

actions specified in this paragraph. 

(l) Retained Exceptions to Service 

Information 

This paragraph restates the requirements of 

paragraph (l) of AD 2011–09–03, Amendment 


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39–16665 (76 FR 22311, April 21, 2011), with 

revised service information. Where Lockheed 

Service Bulletin 382–57–82, Revision 4, 

including Appendixes A, B, and C, dated 

May 20, 2009; or Lockheed Martin 

Aeronautics Company Service Bulletin 382– 

57–82, Revision 6, including Appendixes A, 

B, and C, dated July 11, 2013; specifies to 

contact the manufacturer for disposition of 

certain repair conditions or does not specify 

corrective actions if certain conditions are 

found, this AD requires repairing those 

conditions using a method approved by the 

Manager, Atlanta Aircraft Certification Office 

(ACO), FAA. For a repair method to be 

approved by the Manager, Atlanta ACO, as 

required by this paragraph, the Manager’s 

approval letter must specifically refer to this 

AD. 

(m) New Requirement: Reduced Initial 

Compliance Time for Upper Rainbow 

Fittings 

At the applicable compliance time 

specified in paragraphs (m)(1) and (m)(2) of 

this AD, do eddy current inspections to 

detect cracking of the center wing upper 

rainbow fittings on the left and right side of 

the airplane. Do the actions in accordance 

with the Accomplishment Instructions of 

Lockheed Martin Aeronautics Company 

Service Bulletin 382–57–82, Revision 6, 

including Appendixes A and B, dated July 

11, 2013. If any crack is found during the 

inspections required by this paragraph, 

before further flight, do the actions required 

by paragraph (k) of this AD. Doing the 

requirements of this paragraph terminates the 

requirements of paragraph (g) of this AD for 

that upper rainbow fitting only. Repeat the 

inspection thereafter at the interval required 

by paragraph (n) of this AD. 

(1) For upper rainbow fittings that have 

accumulated less than 10,000 total flight 

hours as of the effective date of this AD, the 

compliance time is at the later of the times 

in paragraphs (m)(1)(i) and (m)(1)(ii) of this 

AD. 

(i) Before the accumulation of 10,000 total 

flight hours. 

(ii) Within 365 days or 600 flight hours 

after the effective date of this AD, whichever 

occurs first. 

(2) For upper rainbow fittings that have 

accumulated 10,000 total flight hours or 

more, but less than 15,000 total flight hours 

as of the effective date of this AD, the 

compliance time is the earlier of the times 

specified in paragraphs (m)(2)(i) and 

(m)(2)(ii) of this AD. 

(i) Within 365 days or 600 flight hours after 

the effective date of this AD, whichever 

occurs first. 

(ii) Before the accumulation of 15,000 total 

flight hours on the rainbow fitting. 

(n) New Requirement: Reduced Repetitive 

Inspection Intervals 

For upper rainbow fittings on which the 

requirements of paragraph (g), (h), or (m) of 

this AD were done, do the next inspection at 

the earlier of the times required in 

paragraphs (n)(1) and (n)(2) of this AD. 

Thereafter, repeat the inspection required by 

paragraph (m) of this AD at intervals not to 

exceed 2,500 flight hours until the upper 

rainbow fitting has accumulated 30,000 total 

flight hours. If any crack is found during the 

inspections required by this paragraph, 

before further flight, do the actions required 

by paragraph (k) of this AD. Doing an 

inspection required by this paragraph 

terminates the requirements of paragraph (h) 

of this AD for the affected upper rainbow 

fitting only. 

(1) Within 3,600 flight hours since the last 

inspection done in accordance with 

paragraph (g), (h), or (m) of this AD, 

whichever occurs latest. 

(2) At the later of the times specified in 

paragraphs (n)(2)(i) and (n)(2)(ii) of this AD. 

(i) Within 2,500 flight hours after the last 

inspection done in accordance with 

paragraph (g), (h), or (m) of this AD, 

whichever occurs latest. 

(ii) Within 365 days or 600 flight hours 

after the effective date of this AD, whichever 

occurs first. 

(o) New Requirement: Reduced PostReplacement Repetitive Inspections 

For upper rainbow fittings replaced in 

accordance with paragraph (i) or (k) of this 

AD, do the inspection required by paragraph 

(m) of this AD at the earlier of the 

compliance times required in paragraph 

(o)(1) and (o)(2) of this AD. Repeat the 

inspection thereafter at intervals not to 

exceed 2,500 flight hours. Doing the 

inspections required by this paragraph 

terminates the requirements of paragraph (j) 

of this AD for the affected upper rainbow 

fitting only. 

(1) At the later of the times in paragraphs 

(o)(1)(i) and (o)(1)(ii) of this AD. (i) Within 

10,000 total flight hours on the upper 

rainbow fitting. 

(ii) Within 365 days or 600 flight hours 

after the effective date of this AD, whichever 

occurs first. 

(2) Within 15,000 total flight hours on the 

upper rainbow fitting. 

(p) Credit for Previous Actions 

The service information identified in 

paragraphs (p)(1)(i), (p)(1)(ii), (p)(1)(iii), 

(p)(2), and (p)(3) is not incorporated by 

reference in this AD. 

(1) This paragraph provides credit for 

actions required by paragraphs (g), (h), (i), (j), 

and (k) of this AD, if those actions were 

performed before the effective date of this AD 

using the service information identified in 

paragraphs (p)(1)(i), (p)(1)(ii), and (p)(1)(iii) 

of this AD. 

(i) Lockheed Service Bulletin 382–57–82, 

including Appendixes A and B, dated 

December 7, 2004. 

(ii) Lockheed Service Bulletin 382–57–82, 

Revision 1, including Appendixes A and B, 

dated February 24, 2005. 

(iii) Lockheed Service Bulletin 382–57–82, 

Revision 2, including Appendixes A and B, 

dated February 15, 2007. 

(2) This paragraph restates paragraph (m) 

of AD 2011–09–03, Amendment 39–16665 

(76 FR 22311, April 21, 2011). This 

paragraph provides credit for actions 

required by paragraphs (g), (h), (i), (j), and (k) 

of this AD, if those actions were performed 

before May 26, 2011 (the effective date of AD 

2011–09–03), using Lockheed Service 

Bulletin 382–57–82, Revision 3, including 

Appendixes A, B, and C, dated April 25, 

2008. 

(3) This paragraph provides credit for 

actions required by paragraphs (g), (h), (i), (j), 

(k), (m), (n), and (o) of this AD, if those 

actions were performed before the effective 

date of this AD using Lockheed Service 

Bulletin 382–57–82, Revision 5, including 

Appendixes A, B, and C, dated August 12, 

2010. 

(q) 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 (r)(2) 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) AMOCs approved for AD 2011–09–03, 

Amendment 39–16665 (76 FR 22311, April 

21, 2011), are approved as AMOCs for the 

corresponding provisions of this AD. 

(r) 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: 404–474–5606; 

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

(2) For information about AMOCs, contact 

Hal Horsbough, 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: hal.horsbough@faa.gov. 

(s) 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. 

(3) The following service information was 

approved for IBR on May 14, 2015. 

(i) Lockheed Martin Aeronautics Company 

Service Bulletin 382–57–82, Revision 6, 

including Appendixes A, B, and C, dated July 

11, 2013. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on May 26, 2011 (76 FR 

22311, April 21, 2011). 

(i) Lockheed Service Bulletin 382–57–82, 

Revision 4, including Appendixes A, B, and 

C, dated May 20, 2009. 

(ii) Reserved. 

(5) For service information identified in 

this AD, contact Lockheed Martin 

Corporation/Lockheed Martin Aeronautics 

Company, Airworthiness Office, Dept. 6A0M, 


Rmajette on DSK2VPTVN1PROD with RULES
Federal Register / Vol. 80, No. 68 / Thursday, April 9, 2015 / Rules and Regulations 19017 

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. 

(6) You may view this service information 

at 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. 

(7) 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 

12, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–06785 Filed 4–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0839; Directorate 

Identifier 2015–CE–006–AD; Amendment 

39–18131; AD 2015–07–03] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Cessna Aircraft Company (Cessna) 

Model 402C and 414A airplanes. This 

AD requires repetitively inspecting the 

engine mount beams for cracks and 

contacting Cessna for FAA-approved 

corrective action if cracks are found. 

This AD also requires sending an 

inspection report to the FAA and to 

Cessna. This AD was prompted by 

reports of cracks found across the 

engine mount beams. We are issuing 

this AD to correct the unsafe condition 

on these products. 

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. 

We must receive comments on this 

AD by May 26, 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: 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 AD, contact Cessna Aircraft 

Company, Customer service, P.O. Box 

7706, Wichita, KS 67277; telephone: 

(316) 517–5800; fax: (316) 517–7271; 

email: customercare@

cessna.textron.com; Internet: http://

www.cessnasupport.com. You may 

review this 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0839. 

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– 

0839; 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 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: Gary 

Park, Aerospace Engineer, Wichita 

Aircraft Certification Office, FAA, 1801 

S. Airport Road, Room 100, Wichita, 

Kansas 67209; phone: (316) 946–4123; 

fax: (316) 946–4107; email: gary.park@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received reports of cracks found 

on the engine mount beams of certain 

Cessna Aircraft Company (Cessna) 

Model 402C airplanes. The cracks found 

run across the beam and extend beyond 

the doubler located under the aft engine 

mount and aft of the forward engine 

mount. Investigation revealed that the 

cause of the cracks is fatigue. 

The engine beam mounts of the 

Cessna Model 402C airplanes are the 

same type design as that of the Cessna 

Model 414A airplanes. 

This condition, if not detected and 

corrected, could result in failure of an 

engine mount beam and could lead to 

engine separation with consequent loss 

of power and loss of control. We are 

issuing this AD to correct the unsafe 

condition on these products. 

Relevant Service Information Under 1 

CFR Part 51 

We reviewed Cessna Aircraft 

Company Multi-engine Service Letter 

No. MEL–54–01, dated March 20, 2015, 

including the undated Attachment, 

‘‘Inspection Results Form.’’ The Cessna 

Aircraft Company Multi-engine Service 

Letter describes procedures for 

inspecting the engine mount beams for 

cracks and reporting the inspection 

results to Cessna. This information is 

reasonably available at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0839, or you may see ADDRESSES for 

other ways to access this service 

information. 

FAA’s Determination 

We are issuing 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. 

AD Requirements 

This AD requires repetitively 

inspecting the engine mount beams for 

cracks and contacting Cessna for an 

FAA-approved corrective action if 

cracks are found. This AD also requires 

sending the inspection results to the 

FAA and to Cessna. 

Differences Between This AD and the 

Service Information 

Cessna Aircraft Company Multiengine Service Letter No. MEL–54–01, 

dated March 20, 2015, including the 

undated Attachment, ‘‘Inspection 

Results Form,’’ specifies reporting the 

inspection results to Cessna. In this AD, 

we also require that the inspection 

results be reported to the FAA. 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 


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