Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations 57053 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (m) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6577; fax: 425–917– 

6590; email: berhane.alazar@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the addresses specified in 

paragraphs (n)(3) and (n)(4) of this AD. 

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Service Bulletin 767–57A0131, 

Revision 1, dated May 8, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

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

Issued in Renton, Washington, on August 

23, 2013. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–22414 Filed 9–16–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0097; Directorate 

Identifier 2011–NM–243–AD; Amendment 

39–17572; AD 2013–17–08] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2010–20– 

08, which applied to certain The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747–400, 747– 

400D, 747–400F, and 747SR series 

airplanes. AD 2010–20–08 required 

repetitive inspections to find cracking of 

the web, strap, inner chords, inner 

chord angle of the forward edge frame 

of the number 5 main entry door 

cutouts; the frame segment between 

stringers 16 and 31; repair if necessary; 

and repetitive inspections for cracking 

of repairs. This new AD expands the 

previous fuselage areas that are 

inspected for cracking. This AD was 

prompted by multiple reports of 

cracking outside of the previous 

inspection areas and a report of a crack 

that initiated at the aft edge of the inner 

chord rather than initiating at a fastener 

location. We are issuing this AD to 

detect and correct such cracks, which 

could cause damage to the adjacent 

body structure and could result in 

depressurization of the airplane in 

flight. 

DATES: This AD is effective October 22, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of October 22, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of November 9, 2010 (75 FR 

61337, October 5, 2010). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of September 12, 2001 (66 FR 

41440, August 8, 2001). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may 

review copies of the 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. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

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

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6428; 

fax: 425–917–6590; email: 

Nathan.P.Weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, 

October 5, 2010) (‘‘AD 2010–20–08)’’. 

AD 2010–20–08 applied to the specified 

products. The NPRM published in the 

Federal Register on March 6, 2013 (78 

FR 14469). The NPRM proposed to 

require repetitive inspections to find 

cracking of the web, strap, inner chords, 

inner chord angle of the forward edge 

frame of the number 5 main entry door 

cutouts; the frame segment between 

stringers 16 and 31; repair if necessary; 

and repetitive inspections for cracking 

of repairs. The NPRM also proposed to 

expand the previous fuselage areas that 

are inspected for cracking. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

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57054 Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations 

following presents the comments 

received on the proposal (78 FR 14469, 

March 6, 2013) and the FAA’s response 

to each comment. 

Support for the NPRM (78 FR 14469, 

March 6, 2013) 

Boeing stated that it concurs with the 

contents of the NPRM (78 FR 14469, 

March 6, 2013). 

Request To Change Repair Procedure 

UPS requested that we revise 

paragraph (q) of the NPRM (78 FR 

14469, March 6, 2013) to allow repairs 

in accordance with Boeing Alert Service 

Bulletin 747–53A2450, Revision 7, 

dated November 2, 2011, instead of only 

the alternative method of compliance 

process. UPS asserted that Boeing Alert 

Service Bulletin 747–53A2450, Revision 

7, dated November 2, 2011, provides 

instructions to repair crack findings for 

the initial and post-repair inspections 

required by the NPRM. 

We partially agree with the 

commenter’s request. We agree that the 

crack repair for the initial and repetitive 

inspections required by paragraph (o) of 

this final rule is addressed by Boeing 

Alert Service Bulletin 747–53A2450, 

Revision 7, dated November 2, 2011. 

However, post-repair cracking is not 

covered by Boeing Alert Service 

Bulletin 747–53A2450, Revision 7, 

dated November 2, 2011. We have 

redesignated paragraph (q) of the NPRM 

as paragraphs (q)(1) and (q)(2) in this 

final rule. We have changed paragraph 

(q)(1) of this final rule to specify that the 

initial inspection crack repair for 

paragraph (o) of this final rule is to be 

done in accordance with Boeing Alert 

Service Bulletin 747–53A2450, Revision 

7, dated November 2, 2011. We have not 

changed the crack repair procedure for 

the post-repair inspection required by 

paragraph (q)(2) of this final rule. 

Changes Made to This Final Rule 

We have redesignated paragraph (r) of 

the NPRM (78 FR 14469, March 6, 2013) 

as paragraph (r)(1) in this final rule, and 

have added paragraph (r)(2) in this final 

rule to clarify certain post-repair 

inspection procedures. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

14469, March 6, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 14469, 

March 6, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 151 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

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

operators 

Inspections [actions retained 

from AD 2010–20–08, 

Amendment 39–16442 (75 

FR 61337, October 5, 

2010)].

Up to 44 work-hours × $85 

per hour = $3,740 per inspection cycle.

$0 Up to $3,740 per inspection 

cycle.

Up to $564,740 per inspection 

cycle. 

Inspections [new action] ......... Up to 121 work-hours × $85 

per hour = $10,285 per inspection cycle.

0 Up to $10,285 per inspection 

cycle.

Up to $1,553,035 per inspection cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2010–20–08, Amendment 39–16442 (75 

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Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations 57055 

FR 61337, October 5, 2010), and adding 

the following new AD: 

2013–17–08 The Boeing Company: 

Amendment 39–17572; Docket No. 

FAA–2013–0097; Directorate Identifier 

2011–NM–243–AD. 

(a) Effective Date 

This AD is effective October 22, 2013. 

(b) Affected ADs 

This AD supersedes AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–100B, 747–100B SUD, 

747–200B, 747–200C, 747–200F, 747–300, 

747–400, 747–400D, 747–400F, and 747SR 

series airplanes, certificated in any category, 

having line numbers 1 through 1419 

inclusive; except for Model 747–400 series 

airplanes that have been modified into the 

Model 747–400 large cargo freighter 

configuration. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by multiple reports 

of cracking outside of the previous inspection 

areas and a report of a crack that initiated at 

the aft edge of the inner chord rather than 

initiating at a fastener location. We are 

issuing this AD to detect and correct such 

cracks, which could cause damage to the 

adjacent body structure and could result in 

depressurization of the airplane in flight. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repetitive Inspections for 

Frame Segment Between Stringers 23 and 31 

(No Terminating Action) 

This paragraph restates the requirements of 

paragraph (g) of AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010). For airplanes having line numbers 

1 through 1304 inclusive: Inspect the 

airplane for cracks between stringers 23 and 

31 per Boeing Alert Service Bulletin 747– 

53A2450, Revision 2, including Appendix A, 

dated January 4, 2001; or Boeing Alert 

Service Bulletin 747–53A2450, Revision 5, 

dated January 29, 2009; at the later of the 

applicable times specified in paragraph (h) or 

(i) of this AD, per table 1 to paragraphs (g) 

and (h) of this AD. Where there are 

differences between the AD and Boeing Alert 

Service Bulletin 747–53A2450, Revision 2, 

including Appendix A, dated January 4, 

2001; or Boeing Alert Service Bulletin 747– 

53A2450, Revision 5, dated January 29, 2009; 

the AD prevails. 

TABLE 1 TO PARAGRAPHS (G) AND (H) OF THIS AD—INSPECTION REQUIREMENTS

Type of Inspection Area to Inspect 

(1) Detailed Visual .............................................. Strap inner chords forward and aft of the web, and exposed web adjacent to the inner chords 

on station 2231 frame from stringers 23 through 31 per Figure 5 or Figure 6 of the service 

bulletins specified in paragraph (g) or (h) of this AD, as applicable. 

(2) Surface High Frequency Eddy Current 

(HFEC).

Station 2231 inner chord angles at lower main sill interface per Figure 5 or Figure 6 of the 

service bulletins specified in paragraph (g) or (h) of this AD, as applicable. 

(3) Open Hole HFEC .......................................... Station 2231 frame fastener locations per Figures 4 and 7, and either Figure 5 or 6 of the 

service bulletins specified in paragraph (g) or (h) of this AD, as applicable. 

(4) Surface HFEC ............................................... Around fastener locations on station 2231 inner chords from stringers 23 through 31 per Figure 5 or Figure 6 of the service bulletins specified in paragraph (g) or (h) of this AD, as applicable. 

(5) Low Frequency Eddy Current (LFEC) .......... Station 2231 frame strap in areas covered by the reveal per Figure 5 or Figure 6 of the service bulletins specified in paragraph (g) or (h) of this AD, as applicable. 

Note 1 to paragraph (g) of this AD: There 

is no terminating action currently available 

for the inspections required by paragraph (g) 

of this AD. 

(h) Retained Compliance Times 

This paragraph restates the requirements of 

paragraph (h) of AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010). Do the inspections specified in 

paragraph (g) of this AD at the applicable 

times specified in paragraph (h)(1) or (h)(2) 

of this AD. Repeat the inspections at intervals 

not to exceed 3,000 flight cycles until the 

inspections required by paragraph (m) or (o) 

of this AD are done. Where there are 

differences between the AD and Boeing Alert 

Service Bulletin 747–53A2450, Revision 2, 

including Appendix A, dated January 4, 

2001; or Boeing Alert Service Bulletin 747– 

53A2450, Revision 5, dated January 29, 2009; 

the AD prevails. 

(1) Do the inspections per table 1 to 

paragraphs (g) and (h) of this AD at the 

applicable time specified in the logic diagram 

in Figure 1 of Boeing Alert Service Bulletin 

747–53A2450, Revision 2, including 

Appendix A, dated January 4, 2001. Where 

the compliance time in the logic diagram 

specifies a compliance time beginning ‘‘from 

receipt of this service bulletin,’’ this AD 

requires that the compliance time begin 

‘‘after September 12, 2001 (the effective date 

of AD 2001–16–02, Amendment 39–12370 

(66 FR 41440, August 8, 2001)).’’ 

(2) After November 9, 2010 (the effective 

date of AD 2010–20–08, Amendment 39– 

16442 (75 FR 61337, October 5, 2010)), do the 

inspections per table 1 to paragraphs (g) and 

(h) of this AD at the applicable compliance 

time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2450, Revision 5, dated 

January 29, 2009. Where the compliance time 

in Boeing Alert Service Bulletin 747– 

53A2450, Revision 2, including Appendix A, 

dated January 4, 2001, specifies a compliance 

time beginning ‘‘after the date on Revision 2 

of this service bulletin,’’ this AD requires that 

the compliance time begin ‘‘after September 

12, 2001 (the effective date of AD 2001–16– 

02, Amendment 39–12370 (66 FR 41440, 

August 8, 2001)).’’ 

(i) Retained Repetitive Inspections for Frame 

Segment Between Stringers 23 and 31 

This paragraph restates the requirements of 

paragraph (i) of AD 2010–20–08, Amendment 

39–16442 (75 FR 61337, October 5, 2010). 

Within 3,000 flight cycles after 

accomplishment of the inspections specified 

in Figure 1 of Boeing Alert Service Bulletin 

747–53A2450, dated May 4, 2000; or Boeing 

Alert Service Bulletin 747–53A2450, 

Revision 1, dated July 6, 2000; repeat the 

inspections specified in paragraph (g) of this 

AD at intervals not to exceed 3,000 flight 

cycles until the inspections required by 

paragraph (m) or (o) of this AD are done. 

Where there are differences between the AD 

and Boeing Alert Service Bulletin 747– 

53A2450, Revision 2, dated January 4, 2001; 

or Boeing Alert Service Bulletin 747– 

53A2450, Revision 5, dated January 29, 2009; 

the AD prevails. 

(j) Retained Additional Repetitive 

Inspections (For Frame Segment Between 

Stringers 16 and 23) 

This paragraph restates the requirements of 

paragraph (j) of AD 2010–20–08, Amendment 

39–16442 (75 FR 61337, October 5, 2010). 

(1) For all airplanes: Before the 

accumulation of 16,000 total flight cycles, or 

within 1,500 flight cycles after November 9, 

2010 (the effective date of AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010)), whichever occurs later, do a 

detailed inspection, an open hole HFEC 

inspection, a surface HFEC inspection, and a 

subsurface LFEC inspection for cracking of 

the forward edge frame of the number 5 main 

entry door cutouts, at station 2231, between 

stringers 16 and 23; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2450, Revision 5, 

dated January 29, 2009. Repeat the 

inspections thereafter at intervals not to 

exceed 3,000 flight cycles. 

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(2) The part number of the nut for fastener 

code ‘‘K’’ in Figure 7 of Boeing Alert Service 

Bulletin 747–53A2450, Revision 5, dated 

January 29, 2009, should be 

‘‘BACN10JC3CD,’’ instead of 

‘‘BACB30JC3CD.’’ In addition, the part 

number of the optional nut for this fastener 

code should be ‘‘BACN10YR3CD,’’ instead of 

‘‘BACN10YR4CD,’’ in Boeing Alert Service 

Bulletin 747–53A2450, Revision 5, dated 

January 29, 2009. 

(k) Retained Repetitive Inspections for Line 

Numbers 1305 and On (For Frame Segment 

Between Stringers 23 and 31) 

This paragraph restates the requirements of 

paragraph (k) of AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010). For airplanes having line numbers 

1305 and on: Before the accumulation of 

16,000 total flight cycles, or within 1,500 

flight cycles after November 9, 2010 (the 

effective date of AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010)), whichever occurs later, do a 

detailed inspection, an open hole HFEC 

inspection, a surface HFEC inspection, and a 

subsurface LFEC inspection for cracking of 

the forward edge frame of the number 5 main 

entry door cutouts, at station 2231, between 

stringers 23 and 31; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2450, Revision 5, 

dated January 29, 2009. Repeat the 

inspections thereafter at intervals not to 

exceed 3,000 flight cycles. 

(l) Retained Corrective Action for 

Paragraphs (g), (j), and (k) of This AD 

This paragraph restates the requirements of 

paragraph (l) of AD 2010–20–08, Amendment 

39–16442 (75 FR 61337, October 5, 2010). If 

any crack is found during any inspection 

required by paragraph (g), (j), or (k) of this 

AD, before further flight, repair the crack in 

accordance with a method approved by the 

Manager, Seattle Aircraft Certification Office 

(ACO), FAA, in accordance with data 

meeting the type certification basis of the 

airplane approved by the Boeing Commercial 

Airplanes Organization Designation 

Authorization (ODA) that has been 

authorized by the Manager, Seattle ACO, to 

make those findings; or in accordance with 

Boeing Alert Service Bulletin 747–53A2450, 

Revision 5, dated January 29, 2009; as 

applicable. For a repair method to be 

approved by the Manager, Seattle ACO, as 

required by this paragraph, the approval 

letter must specifically reference this AD. As 

of November 9, 2010 (the effective date of AD 

2010–20–08), repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (s) of this AD. 

(m) Retained Post-Repair Inspections 

This paragraph restates the requirements of 

paragraph (m) of AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010). Except as required by paragraph (n) 

of this AD, for airplanes on which the 

forward edge frame of the number 5 main 

entry door cutouts, at station 2231, between 

stringers 16 and 31, is repaired as specified 

in Boeing Alert Service Bulletin 747– 

53A2450: Within 3,000 flight cycles after 

doing the repair, or within 1,500 flight cycles 

after November 9, 2010 (the effective date of 

AD 2010–20–08), whichever occurs later, do 

the detailed, LFEC, and HFEC inspections of 

the repaired area for cracks, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2450, 

Revision 5, dated January 29, 2009. If no 

cracking is found, repeat the inspections 

thereafter at intervals not to exceed 3,000 

flight cycles. If any crack is found: Before 

further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (s) of this AD. Doing 

the inspections specified in paragraph (m) of 

this AD terminates the repetitive inspections 

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

of this AD for the repaired area. 

(n) Retained Post-Repair Inspection 

Restriction 

This paragraph restates the requirements of 

paragraph (n) of AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010). For any frame that is repaired in 

accordance with a method other than the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2450, Revision 5, 

dated January 29, 2009: Do the inspection in 

accordance with a method approved in 

accordance with the procedures specified in 

paragraph (s) of this AD. 

(o) New Repetitive Inspections With 

Expanded Inspection Area 

Before the accumulation of 16,000 total 

flight cycles, or within 3,000 flight cycles 

after the effective date of this AD, whichever 

occurs later, do the inspections required by 

paragraphs (o)(1) through (o)(5) of this AD, 

except as specified in paragraph (p) of this 

AD. Do all actions required by this paragraph 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2450, Revision 7, dated November 2, 

2011. Repeat the inspections thereafter at the 

applicable times specified in Paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2450, Revision 7, dated 

November 2, 2011. Accomplishment of the 

initial inspections required by this paragraph 

terminates the requirements of paragraphs (g) 

through (k) of this AD. 

(1) Do a detailed inspection for cracking on 

the frame strap, inner chords forward and aft 

of the web, and exposed web adjacent to the 

inner chords from stringer 15 to 31. 

(2) Do an HFEC inspection of the station 

2231 frame fastener locations for cracking 

from stringer 16 to 31, including locations 

common to the upper main sill strap and 

stringer clip at stringer 16. 

(3) Do an HFEC inspection for cracking of 

the frame inner chords around the fastener 

heads from stringer 15 to 31. 

(4) Do an HFEC inspection for cracking of 

the aft edge of the aft inner chord, of the 

forward edge of the forward inner chord, and 

of the forward and aft edges of the frame 

strap from stringer 15 to 31. 

(5) Do an LFEC inspection for cracking of 

the station 2231 frame strap from stringer 16 

to 31 in areas covered by the reveal. 

(p) New Post-Repair Inspection for Repaired 

Areas 

For airplanes on which the post-repair 

inspections are being done as specified in 

paragraph (m) of this AD: For the repaired 

area only, continue the inspections as 

specified in paragraph (m) of this AD in lieu 

of the inspections specified in paragraph (o) 

of this AD. 

(q) New Corrective Action 

(1) If any cracking is found during any 

inspection required by paragraph (o) of this 

AD: Before further flight, repair the cracking, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2450, Revision 7, dated November 2, 

2011. 

(2) If any cracking is found during any 

inspection required by paragraph (p) or (r) of 

this AD: Before further flight, repair the 

cracking using a method approved in 

accordance with the procedures specified in 

paragraph (s) of this AD. 

(r) New Post-Repair Repetitive Inspections 

and Corrective Action 

(1) For any airplane repaired as specified 

in paragraph (q)(1) of this AD: Within 3,000 

flight cycles after doing the repair, do 

detailed, LFEC, and HFEC inspections of the 

repaired area for cracking, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2450, 

Revision 7, dated November 2, 2011. If no 

cracking is found, repeat the inspections 

thereafter at intervals not to exceed 3,000 

flight cycles. If any cracking is found: Before 

further flight, repair the cracking using a 

method approved in accordance with the 

procedures specified in paragraph (s) of this 

AD. 

(2) For any airplane repaired as specified 

in paragraph (q)(2) of this AD: Before further 

flight, contact the Manager, Seattle Aircraft 

Certification Office (ACO), FAA, for 

instructions and compliance times for doing 

an inspection of the repaired area for 

cracking. Do the inspection at the compliance 

times specified using the inspection 

procedures provided. If any cracking is 

found: Before further flight, repair the 

cracking using a method approved in 

accordance with the procedures specified in 

paragraph (s) of this AD. 

(s) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes ODA that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

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Federal Register / Vol. 78, No. 180 / Tuesday, September 17, 2013 / Rules and Regulations 57057 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010), are approved as AMOCs for the 

corresponding provisions of paragraphs (g) 

through (m) of this AD. 

(5) AMOCs approved previously in 

accordance with AD 2010–20–08, 

Amendment 39–16442 (75 FR 61337, October 

5, 2010), that have post-repair inspections are 

approved as AMOCs for the corresponding 

provisions of paragraph (o) of this AD for the 

repaired area only. 

(t) Related Information 

For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6428; fax: 425– 

917–6590; email: 

Nathan.P.Weigand@faa.gov. 

(u) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on October 22, 2013. 

(i) Boeing Alert Service Bulletin 747– 

53A2450, Revision 7, dated November 2, 

2011. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on November 9, 2010 (75 

FR 61337, October 5, 2010). 

(i) Boeing Alert Service Bulletin 747– 

53A2450, Revision 5, dated January 29, 2009. 

(ii) Reserved. 

(5) The following service information was 

approved for IBR on September 12, 2001 (66 

FR 441440, August 8, 2001). 

(i) Boeing Alert Service Bulletin 747– 

53A2450, Revision 2, including Appendix A, 

dated January 4, 2001. 

(ii) Reserved. 

(6) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https:// 

www.myboeingfleet.com. 

(7) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(8) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

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

Issued in Renton, Washington, on August 

16, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–22408 Filed 9–16–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES 

Food and Drug Administration 

21 CFR Part 520 

[Docket No. FDA–2013–N–0002] 

Oral Dosage Form New Animal Drugs; 

Amprolium; Meloxicam 

AGENCY: Food and Drug Administration, 

HHS. 

ACTION: Final rule. 

SUMMARY: The Food and Drug 

Administration (FDA) is amending the 

animal drug regulations to reflect 

approval actions for new animal drug 

applications (NADAs) and abbreviated 

new animal drug applications 

(ANADAs) during August 2013. FDA is 

also informing the public of the 

availability of summaries of the basis of 

approval and of environmental review 

documents, where applicable. 

DATES: This rule is effective September 

17, 2013. 

FOR FURTHER INFORMATION CONTACT: 

George K. Haibel, Center for Veterinary 

Medicine (HFV–6), Food and Drug 

Administration, 7519 Standish Pl., 

Rockville, MD 20855, 240–276–9019, 

george.haibel@fda.hhs.gov. 

SUPPLEMENTARY INFORMATION: FDA is 

amending the animal drug regulations to 

reflect approval actions for NADAs and 

ANADAs during August 2013, as listed 

in table 1. In addition, FDA is informing 

the public of the availability, where 

applicable, of documentation of 

environmental review required under 

the National Environmental Policy Act 

(NEPA) and, for actions requiring 

review of safety or effectiveness data, 

summaries of the basis of approval (FOI 

Summaries) under the Freedom of 

Information Act (FOIA). These public 

documents may be seen in the Division 

of Dockets Management (HFA–305), 

Food and Drug Administration, 5630 

Fishers Lane, Rm. 1061, Rockville, MD 

20852, between 9 a.m. and 4 p.m., 

Monday through Friday. Persons with 

access to the Internet may obtain these 

documents at the CVM FOIA Electronic 

Reading Room: http://www.fda.gov/

AboutFDA/CentersOffices/

OfficeofFoods/CVM/

CVMFOIAElectronicReadingRoom/

default.htm. 

This rule does not meet the definition 

of ‘‘rule’’ in 5 U.S.C. 804(3)(A) because 

it is a rule of ‘‘particular applicability.’’ 

Therefore, it is not subject to the 

congressional review requirements in 5 

U.S.C. 801–808. 

TABLE 1—ORIGINAL AND SUPPLEMENTAL NADAS AND ANADAS APPROVED DURING AUGUST 2013 

NADA/

ANADA Sponsor New Animal Drug Product Name Action 21 CFR Section 

FOIA 

Summary 

NEPA 

Review 

200–514 ... Phibro Animal Health Corp., 

GlenPointe Centre East, 

3d floor, 300 Frank W. 

Burr Blvd., Suite 21, Teaneck, NJ 07666.

BOVIPROL (amprolium) 

9.6% Oral Solution.

Original approval as a generic copy of NADA 13– 

149.

520.100 Yes ..... CE1. 

200–550 ... Ceva Sante Animale, 10 Avenue de la Ballastie ́re 

33500 Libourne, France.

MELOXIDYL (meloxicam) 

Oral Suspension.

Original approval as a generic copy of NADA 141– 

213.

520.1350 Yes ..... CE1. 

1The Agency has determined under 21 CFR 25.33(a)(1) that this action is categorically excluded (CE) from the requirement to submit an environmental assessment or an environmental impact statement because it is of a type that does not individually or cumulatively have a significant 

effect on the human environment. 

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