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

(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 Co ˆ te 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.


## 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 fittingsduring 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:


## 55677 Federal Register / Vol. 79, No. 180 / Wednesday, September 17, 2014 / Proposed Rules

E STIMATED 

### 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


## 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.


## 55679 Federal Register / Vol. 79, No. 180 / Wednesday, September 17, 2014 / Proposed Rules

(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 prescribesprocedures 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