Federal Register / Vol. 75, No. 55 / Tuesday, March 23, 2010 / Proposed Rules 13695 

MRB–145/1150, Revision 11, dated 

September 19, 2007; and the Parker CMMs 

listed in Table 2 of this AD; for related 

information. 

Issued in Renton, Washington on March 

16, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–6309 Filed 3–22–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0233; Directorate 

Identifier 2009–NM–014–AD] 

RIN 2120–AA64 

Airworthiness Directives; Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company Model 382, 

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

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

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

airplanes. This proposed AD would 

require 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. This proposed AD results 

from a report 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 are proposing this 

AD 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. 

DATES: We must receive comments on 

this proposed AD by May 7, 2010. 

ADDRESSES: You may send comments 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 proposed AD, contact Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company, Airworthiness 

Office, Dept. 6A0M, Zone 0252, Column 

P–58, 86 S. Cobb Drive, Marietta, 

Georgia 30063; telephone 770–494– 

5444; fax 770–494–5445; e-mail 

ams.portal@lmco.com; Internet http://

www.lockheedmartin.com/ams/tools/

TechPubs.htmlx. You may review 

copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, Washington. 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; 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 

(telephone 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; telephone (404) 474–5554; fax 

(404) 474–5606. 

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–2010–0233; Directorate Identifier 

2009–NM–014–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 

Fatigue cracking of the wing upper 

and lower rainbow fittings during the 

durability test and on in-service 

airplanes indicates a requirement to 

perform inspections prior to the current 

published Hercules Airfreighter Series 

Progressive Inspection Procedures and 

Hercules Airfreighter Progressive 

Inspection Procedures intervals. 

Analysis of in-service cracking has 

shown that these rainbow fittings are 

susceptible to multiple site fatigue 

damage. This condition, if not corrected, 

could lead to the failure of the rainbow 

fittings and a catastrophic failure of the 

center wing. 

Relevant Service Information 

We have reviewed Lockheed Service 

Bulletin 382–57–82, Revision 3, 

including Appendixes A, B, and C, 

dated April 25, 2008. The service 

bulletin describes procedures for 

repetitive eddy current inspections to 

detect cracks in the center wing upper 

and lower rainbow fittings. The service 

bulletin specifies marking and reporting 

suspected cracks but does not provide 

corrective actions. 

The service bulletin also describes 

procedures for repetitively replacing the 

upper and lower rainbow fittings, which 

would extend the interval for the next 

eddy current inspection. The 

replacement includes related 

investigative and corrective actions. The 

related investigative actions consist of 

two types of inspections: (1) A general 

visual inspection for damage and 

defects (including corrosion and 

cracking) of the wing faying structure; 

and (2) a primary automated bolt hole 

eddy current (ABHEC) inspection to 

detect cracks of all opened fitting 

attachment fastener holes in the upper 

and lower surface skin panel, stringers, 

splice straps, and splice angles that are 

common to the rainbow fittings prior to 

installing the new rainbow fitting. The 

service bulletin describes procedures for 

a ‘‘redundant’’ (backup) ABHEC 

inspection of any suspected damage. 

The corrective actions consist of 

repairing confirmed damage within 

certain limits, and contacting the 

manufacturer for damage that exceeds 

those limits. The service bulletin 

provides no corrective actions for 

damage or defects found during the 

visual inspection. 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
13696 Federal Register / Vol. 75, No. 55 / Tuesday, March 23, 2010 / Proposed Rules 

FAA’s Determination and Requirements 

of This Proposed AD 

We are proposing this AD because we 

evaluated all relevant information and 

determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. This proposed AD would 

require accomplishing the actions 

specified in the service information 

described previously, except as 

discussed under ‘‘Differences Between 

the Proposed AD and Service Bulletin.’’ 

The proposed AD would also require 

sending the inspection results to 

Lockheed. 

Differences Between the Proposed AD 

and Service Bulletin 

In Lockheed Service Bulletin 382–57– 

82, Revision 3, dated April 25, 2008, the 

NOTE in paragraph 1.B.(1) states that 

operators who have completed a 

Lockheed Martin usage evaluation 

analysis may adjust the intervals 

provided in the service bulletin by 

severity factors developed for their 

inspection programs. The proposed AD 

would require approval of an alternative 

method of compliance (AMOC) for such 

an adjustment. 

Although the service bulletin 

specifies that operators may contact the 

manufacturer for disposition of certain 

repair conditions and the service 

bulletin does not specify corrective 

actions for damage or cracking found 

during the visual inspection, this 

proposed AD would require operators to 

repair those conditions using a method 

approved by the FAA. 

Although the service bulletin does not 

specify corrective actions for airplanes 

on which cracking is found during the 

eddy current inspections, this proposed 

AD would require operators to replace 

the rainbow fittings if any cracking is 

found. 

Lockheed Service Bulletin 382–57–82, 

Revision 3, dated April 25, 2008, also 

recommends grounding airplanes that 

have accumulated 20,000 or more flight 

hours until inspections are done. We 

have provided a grace period of 365 

days or 600 flight hours after the 

effective date of this AD in paragraph 

(g)(2) of this AD to prevent grounding 

the fleet. This time period does not 

present a safety concern since this area 

is already being inspected at a repetitive 

interval and the inspection to this point 

would have found cracks as intended. 

We find that the short initial inspection 

period provided in the proposed AD 

provides an adequate level of safety. 

Interim Action 

We consider this proposed AD 

interim action. If final action is later 

identified, we might consider further 

rulemaking then. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 14 airplanes of U.S. 

registry. The following table provides 

the estimated costs for U.S. operators to 

comply with this proposed AD. 

TABLE—ESTIMATED COSTS

Action Work hours 

Average 

labor 

rate per 

hour 

Parts Cost per 

airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection .................. 20 $85 None $1,700 per inspection cycle .. 14 $23,800 per inspection cycle. 

Fitting replacement ... 2,438 $85 $40,000 $247,230 ............................... 14 $3,461,220 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), and 

3. 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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company: Docket 

No. FAA–2010–0233; Directorate 

Identifier 2009–NM–014–AD. 

Comments Due Date 

(a) We must receive comments by May 7, 

2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Lockheed Martin 

Corporation/Lockheed Martin Aeronautics 

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

382G airplanes, certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1
Federal Register / Vol. 75, No. 55 / Tuesday, March 23, 2010 / Proposed Rules 13697 

Unsafe Condition 

(e) This AD results from a report of fatigue 

cracking of the wing upper and lower 

rainbow fittings during durability testing and 

on in-service airplanes. Analysis of in-service 

cracking has shown that these rainbow 

fittings are susceptible to multiple site fatigue 

damage. The Federal Aviation 

Administration is issuing this AD 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. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Initial Inspections 

(g) 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 3, including Appendixes A and B, 

dated April 25, 2008. Any cracks found 

during the inspections required by paragraph 

(g) of this AD must be repaired before further 

flight in accordance with the actions required 

by paragraph (l) of this AD. 

(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 the effective date of 

this AD, whichever occurs first. 

Repetitive Inspection Schedule 

(h) 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. Any cracks found 

during the inspections required by paragraph 

(h) of this AD must be repaired before further 

flight in accordance with the actions required 

by paragraph (l) of this AD. 

Rainbow Fitting Replacements 

(i) Before the accumulation of 30,000 flight 

hours on the rainbow fitting or within 600 

flight hours after the effective date of this AD, 

whichever occurs later: Replace the 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 3, 

including Appendix C, dated April 25, 2008. 

Replace the rainbow fitting thereafter at 

intervals not to exceed 30,000 flight hours. 

Post-Replacement Repetitive Inspections 

(j) For upper and lower rainbow fittings 

replaced in accordance with paragraph (i) or 

(k) 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. 

Repair of Damaged Rainbow Fittings and 

Associated Areas 

(k) If, during any inspection required by 

paragraph (g) or (h) of this AD, any crack is 

detected, before further flight, replace the 

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 3, including Appendix C, dated 

April 25, 2008, except as provided by 

paragraph (l) of this AD. 

Exceptions to Service Bulletin 

(l) Where Lockheed Service Bulletin 382– 

57–82, Revision 3, including Appendixes A, 

B, and C, dated April 25, 2008, specifies to 

contact the manufacturer for disposition of 

certain repair conditions, and where the 

service bulletin 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. 

Alternative Methods of Compliance 

(AMOCs) 

(m)(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. Send information to ATTN: 

Carl Gray, Aerospace Engineer, Airframe 

Branch, ACE–117A, FAA, Atlanta Aircraft 

Certification Office, 1701 Columbia Avenue, 

College Park, Georgia 30337; telephone (404) 

474–5554; fax (404) 474–5606. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Issued in Renton, Washington, on March 

17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–6307 Filed 3–22–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2010–0052; Airspace 

Docket No. 10–ASO–13] 

Amendment of Class E Airspace; 

Clemson, SC and Establishment of 

Class E Airspace; Pickens, SC 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

amend Class E airspace at Clemson, SC, 

to correct the airspace description and 

establish Class E airspace at Pickens, 

SC, to achieve an additional 1000’ of 

airspace to support a new LPV 

Approach (Localizer Performance with 

Vertical Guidance) that has been 

developed for Pickens County Airport. 

This action enhances the safety and 

airspace management of ClemsonOconee County Airport, SC and Pickens 

County Airport, Pickens, SC. 

DATES: Comments must be received on 

or before May 7, 2010. 

ADDRESSES: Send comments on this rule 

to: U.S. Department of Transportation, 

Docket Operations, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590–0001; Telephone: 1–800– 

647–5527; Fax: 202–493–2251. You 

must identify the Docket Number FAA– 

2010–0052; Airspace Docket No. 10– 

ASO–13, at the beginning of your 

comments. You may also submit and 

review received comments through the 

Internet at http://www.regulations.gov. 

FOR FURTHER INFORMATION CONTACT: 

Melinda Giddens, Operations Support 

Group, Eastern Service Center, Federal 

Aviation Administration, P.O. Box 

20636, Atlanta, Georgia 30320; 

telephone (404) 305–5610. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested persons are invited to 

comment on this rule by submitting 

such written data, views, or arguments, 

as they may desire. Comments that 

provide the factual basis supporting the 

views and suggestions presented are 

particularly helpful in developing 

reasoned regulatory decisions on the 

proposal. Comments are specifically 

invited on the overall regulatory, 

aeronautical, economic, environmental, 

and energy-related aspects of the 

proposal. 

Communications should identify both 

docket numbers (FAA Docket No. FAA– 


wwoods2 on DSK1DXX6B1PROD with PROPOSALS_PART 1