Federal Register / Vol. 79, No. 180 / Wednesday, September 17, 2014 / Proposed Rules 55675 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. 

airplanes identified in paragraphs (c)(1), 

(c)(2), and (c)(3) of this AD, certificated in 

any category. 

(1) Model CL–600–2A12 (CL–601) 

airplanes, serial numbers 3001 through 3066 

inclusive. 

(2) Model CL–600–2B16 (CL–601–3A, CL– 

601–3R Variants) airplanes, serial numbers 

5001 through 5194 inclusive. 

(3) Model CL–600–2B16 (CL–604 Variant) 

airplanes, serial numbers 5301 through 5665 

inclusive, and 5701 through 5934 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24, Electrical Power. 

(e) Reason 

This AD was prompted by a report of an 

aft equipment bay fire due to chafing and 

subsequent arcing of the integrated drive 

generator (IDG) power cables. Additionally, 

we have received several reports of broken 

support brackets of the hydraulic lines. We 

are issuing this AD to detect and correct 

broken support brackets of the hydraulic 

lines, which could result in inadequate 

clearance between the IDG power cables and 

hydraulic lines and chafing of the IDG power 

cables, and consequent high energy arcing 

and an uncontrolled fire in the aft equipment 

bay. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) One-Time Inspection and Corrective 

Actions 

Within 400 flight hours or 18 months after 

the effective date of this AD, whichever 

occurs first: Perform a one-time detailed 

inspection of the IDG power cables for 

chafing between the cables and the adjacent 

hydraulic and pneumatic lines, and for any 

cracked or broken support bracket of the 

hydraulic lines, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 

If any chafing of the power cables or any 

cracked or broken support bracket is found, 

before further flight, repair or replace, as 

applicable, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 

(1) Bombardier Service Bulletin 605–24– 

007, Revision 01, dated January 13, 2014 (for 

Model CL–600–2B16 airplanes). 

(2) Bombardier Service Bulletin 604–24– 

026, Revision 01, dated January 13, 2014 (for 

Model CL–600–2B16 airplanes). 

(3) Bombardier Service Bulletin 601–0625, 

Revision 01, dated January 13, 2014 (for 

Model Cl-600–2A12 and CL–600–2B16 

airplanes). 

(h) Credit for Previous Actions 

This paragraph provides credit for action 

required by paragraph (g) of this AD, if the 

action was performed before the effective 

date of this AD using Bombardier Service 

Bulletin 605–24–007, 604–24–026, or 601– 

0625, all dated September 18, 2012, provided 

that the action specified in Service Request 

for Product Support Action (SRPSA) 27512, 

SRPSA 30806, SRPSA 32727, SRPSA 32864, 

or SRPSA 33161 has not been done. 

Bombardier Service Bulletins 605–24–007, 

604–24–026, and 601–0625, all dated 

September 18, 2012, are not incorporated by 

reference in this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531. 

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 

Transport Canada Civil Aviation (TCCA), or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–05, dated 

January 20, 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 it in Docket No. 

FAA–2014–0625. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 Coˆte 

Vertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.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 

September 9, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–22151 Filed 9–16–14; 8:45 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] 

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 supersede 

Airworthiness Directive (AD) 2011–09– 

03, which applies to all Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company Model 382, 382B, 

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

2011–09–03 currently requires 

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. Since we issued AD 2011– 

09–03, analysis of in-service cracking 

has shown that a reduction in the 

inspection intervals is necessary for the 

upper rainbow fittings. This proposed 

AD is intended to complete certain 

mandated programs intended to support 

the airplane reaching its limit of validity 

(LOV) of the engineering data that 

support the established structural 

maintenance program. This proposed 

AD would require reduced intervals for 

inspections of the upper rainbow 

fittings. We are proposing 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: We must receive comments on 

this proposed AD by November 3, 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. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
55676 Federal Register / Vol. 79, No. 180 / Wednesday, September 17, 2014 / Proposed Rules 

• 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 

Washington 98057. 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– 

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 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, Georgia 

30337; phone: 404–474–5554; fax: 404– 

474–5606; email: carl.w.gray@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–2014–0627; Directorate Identifier 

2013–NM–217–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On April 12, 2011, we issued AD 

2011–09–03, Amendment 39–16665 (76 

FR 22311, April 21, 2011), for all 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company Model 

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

airplanes. AD 2011–09–03 requires 

repetitive eddy current inspections to 

detect cracks in the center wing upper 

and lower rainbow fittings, and 

corrective actions if necessary; and 

repetitive replacements of rainbow 

fittings, which would extend the 

repetitive interval for the next 

inspection. AD 2011–09–03 resulted 

from reports of fatigue cracking of the 

wing upper and lower rainbow fittings 

during durability testing and on inservice airplanes. Analysis of in-service 

cracking has shown that these rainbow 

fittings are susceptible to multiple site 

fatigue damage. We issued AD 2011–09– 

03 to detect and correct such fatigue 

cracks, which could grow large and lead 

to the failure of the fitting and a 

catastrophic failure of the center wing. 

Actions Since AD 2011–09–03, 

Amendment 39–16665 (76 FR 22311, 

April 21, 2011), Was Issued 

Since we issued AD 2011–09–03, 

Amendment 39–16665 (76 FR 22311, 

April 21, 2011), analysis of in-service 

cracking 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. 

We have also revised paragraphs (i) 

and (k) of AD 2011–09–03, Amendment 

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

to clarify the rainbow fitting is replaced 

with a new rainbow fitting, as specified 

in Lockheed Service Bulletin 382–57– 

82, Revision 4, including Appendixes A 

and B, dated May 20, 2009; and 

Lockheed Service Bulletin 382–57–82, 

including Appendices A and B, 

Revision 6, dated July 11, 2013. 

Relevant Service Information 

We reviewed Lockheed Service 

Bulletin 382–57–82, including 

Appendices A, B, and C, Revision 6, 

dated July 11, 2013. The compliance 

times are reduced, but the procedures 

are unchanged from those described in 

Lockheed Service Bulletin 382–57–82, 

including Appendices A, B, and C, 

dated April 25, 2008. 

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 all of 

the requirements of AD 2011–09–03, 

Amendment 39–16665 (76 FR 22311, 

April 21, 2011). This proposed AD 

would reduce compliance times for 

initial and repetitive inspections of the 

upper rainbow fitting. 

We have clarified the replacement 

process to more closely match the intent 

of the service information to replace 

affected fittings with new replacement 

fittings. 

Differences Between This Proposed AD 

and the Service Information 

Where Lockheed Service Bulletin 

382–57–82, including Appendices A, B, 

and C, Revision 6, dated July 11, 2013, 

does not specify a corrective action or 

states ‘‘taking appropriate corrective 

action,’’ this NPRM proposes to require 

repairing those conditions using a 

method approved by the Manager, 

Atlanta Aircraft Certification Office, 

FAA. 

Costs of Compliance 

We estimate that this proposed AD 

affects 14 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 180 / Wednesday, September 17, 2014 / Proposed Rules 55677 

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.

(1) $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. 

(1) None. 

This proposed 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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would not 

have a substantial direct effect on the 

States, on the relationship between the 

national Government and the States, or 

on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

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) 2011–09– 

03, Amendment 39–16665 (76 FR 

22311, April 21, 2011), and adding the 

following new AD: 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company: Docket 

No. FAA–2014–0627; Directorate 

Identifier 2013–NM–217–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by November 3, 2014. 

(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 Service 

Bulletin 382–57–82, including Appendices A 

and B, Revision 6, 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 

Service Bulletin 382–57–82, including 

Appendices A and B, Revision 6, 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 paragraph (h) of this 

AD, before further flight, do the actions 

required by paragraph (k) of this AD. Doing 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
55678 Federal Register / Vol. 79, No. 180 / Wednesday, September 17, 2014 / Proposed Rules 

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 Service 

Bulletin 382–57–82, including Appendix C, 

Revision 6, 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 

Service Bulletin 382–57–82, including 

Appendix C, Revision 6, 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 Service 

Bulletin 382–57–82, including Appendix C, 

Revision 6, dated July 11, 2013, except as 

required by paragraph (l) of this AD. As of 

the effective date of this AD, only use 

Lockheed Service Bulletin 382–57–82, 

including Appendix C, Revision 6, dated July 

11, 2013, for accomplishing the actions 

specified in this paragraph. 

(l) Retained Exceptions to Service Bulletin 

This paragraph restates the requirements of 

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

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 Service Bulletin 

382–57–82, including Appendices A, B, and 

C, Revision 6, 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 Service Bulletin 382–57–82, 

including Appendices A and B, Revision 6, 

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 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 Appendices A and B, dated 

December 7, 2004. 

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

Revision 1, including Appendices A and B, 

dated February 24, 2005. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 180 / Wednesday, September 17, 2014 / Proposed Rules 55679 

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

Revision 2, including Appendices 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, including Appendices 

A, B, and C, Revision 5, dated August 12, 

2010. 

(q) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta Aircraft 

Certification Office, 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, Georgia 

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, Georgia 

30337; phone: 404–474–5554; fax: 404–474– 

5606; email: hal.horsbough@faa.gov. 

(3) 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. 

Issued in Renton, Washington, on 

September 9, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–22149 Filed 9–16–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF DEFENSE 

Office of the Secretary 

32 CFR Part 238 

[Docket ID: DOD–2012–OS–0075] 

RIN 0790–AI90 

DoD Assistance to Non-Government, 

Entertainment-Oriented Media 

Productions 

AGENCY: Office of the Assistant to the 

Secretary of Defense for Public Affairs, 

DoD. 

ACTION: Proposed rule. 

SUMMARY: This rule establishes policy, 

assigns responsibilities, and prescribes 

procedures for DoD assistance to nonGovernment entertainment media 

productions such as feature motion 

pictures, episodic television programs, 

documentaries, and computer-based 

games. This rule provides for oversight 

of production assistance decisions at 

centralized and senior levels of DoD to 

ensure consistency of approach among 

DoD and Service components with 

respect to support for entertainment 

media productions, including 

documentaries. 

DATES: Comments must be received by 

November 17, 2014. 

ADDRESSES: You may submit comments, 

identified by docket number and or 

Regulatory Information Number (RIN) 

and title, by any of the following 

methods: 

• Federal Rulemaking Portal: http://

www.regulations.gov. Follow the 

instructions for submitting comments. 

• Mail: Federal Docket Management 

System Office, 4800 Mark Center Drive, 

2nd floor, East Tower, Suite 02G09, 

Alexandria VA 22350–3100. 

Instructions: All submissions received 

must include the agency name and 

docket number or RIN for this Federal 

Register document. The general policy 

for comments and other submissions 

from members of the public is to make 

these submissions available for public 

viewing on the Internet at http://

www.regulations.gov as they are 

received without change, including any 

personal identifiers or contact 

information. 

FOR FURTHER INFORMATION CONTACT: 

Philip M. Strub, (703) 695–2936. 

SUPPLEMENTARY INFORMATION: 

Executive Summary 

I. Purpose 

This rule is being published to seek 

comment on DOD’s updated policy for 

support to entertainment-oriented 

media productions, including 

documentaries. The increased and 

higher-level oversight is required to 

eliminate inconsistencies and 

ambiguities in guidance for and 

supervision of DoD activities to ensure 

common standards are met in providing 

support, and that production support is 

appropriate. The rule also includes two 

DoD Production Assistance Memoranda 

(PAM) as samples. These memoranda 

explain the terms under which DoD 

provides assistance to production 

companies for projects that have been 

approved for DoD support. 

II. Summary of the Major Provisions of 

This Regulatory Action 

(a) This rule includes documentaries 

within the category of non-government, 

entertainment-oriented media 

productions and requires approval of 

production assistance for such 

entertainment-oriented media 

productions at the DoD level vice the 

Service level. 

(b) This rule includes two sample 

DoD Production Assistance Memoranda 

(PAMs), one for documentary 

productions and one for all other 

entertainment media productions. This 

rule also assigns the authority for 

signing both types of agreements to the 

Assistant to the Secretary of Defense for 

Public Affairs (ATSD(PA)), or the 

ATSD(PA)’s designee. 

(c) This rule addresses how military 

personnel may appear in entertainment 

media. This rule requires the written 

permission of the Assistant to the 

Secretary of Defense for Public Affairs 

(or his/her designee) in order for active 

duty military personnel to serve as 

actors in significant roles and in roles 

beyond the scope of their normal duties. 

III. Costs and Benefits of This 

Regulatory Action 

First, the support and assistance to 

non-government entertainment media 

productions will be at no additional cost 

to the government and taxpayers. Once 

DoD has agreed with a production 

company to provide production 

assistance and the parties have signed a 

Production Assistance Memorandum, 

operations, and maintenance, supply 

and equipment costs incurred by DoD 

(collectively) as a direct consequence of 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS