Federal Register / Vol. 78, No. 140 / Monday, July 22, 2013 / Rules and Regulations 43763 

10,000 total flight hours, whichever occurs 

first. 

(h) Retained Follow-on Action With Revised 

Service Information 

This paragraph restates the requirements of 

paragraph (h) of AD 2011–13–08, 

Amendment 39–16731 (76 FR 37253, June 

27, 2011), with revised service information. 

If, during the check required by paragraph (g) 

of this AD, the bearing free-play is within the 

limits specified in Bombardier Service 

Bulletin 84–27–52, dated May 25, 2010, or 

Revision A, dated March 5, 2012; no further 

action is required by this AD. As of the 

effective date of this AD, only Bombardier 

Service Bulletin 84–27–52, Revision A, dated 

March 5, 2012, may be used to accomplish 

the actions required by this paragraph. 

(i) Retained Corrective Actions With Revised 

Service Information 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–13–08, Amendment 

39–16731 (76 FR 37253, June 27, 2011), with 

revised service information. If, during the 

check required by paragraph (g) of this AD, 

the bearing free-play exceeds the limits 

specified in Bombardier Service Bulletin 84– 

27–52, dated May 25, 2010; or Revision A, 

dated March 5, 2012: Before further flight, 

replace the elevator PCU with a serviceable 

one, in accordance with paragraph 3.B., Part 

B, of Bombardier Service Bulletin 84–27–52, 

dated May 25, 2010; or Revision A, dated 

March 5, 2012. As of the effective date of this 

AD, only Bombardier Service Bulletin 84– 

27–52, Revision A, dated March 5, 2012, may 

be used to accomplish the actions required 

by this paragraph. 

(j) New Free-Play Check 

For airplanes having S/N 4305 through 

4334 inclusive, and 4336: At the applicable 

time specified in paragraphs (j)(1) and (j)(2) 

of this AD, perform a free-play check for any 

shaft swaged bearing having P/N MS14103– 

7 that is installed in the tailstock end of each 

elevator PCU (three PCUs per elevator 

surface), having P/Ns 390600–1007 and 

390600–1009, in accordance with paragraph 

3.B., Part A, of Bombardier Service Bulletin 

84–27–52, Revision A, dated March 5, 2012. 

(1) For airplanes that have accumulated 

8,000 or more total flight hours as of the 

effective date of this AD: Within 2,000 flight 

hours after the effective date of this AD. 

(2) For airplanes that have accumulated 

less than 8,000 total flight hours as of the 

effective date of this AD: Within 6,000 flight 

hours after the effective date of this AD, or 

before the accumulation of 10,000 total flight 

hours, whichever occurs first. 

(k) New Corrective Actions 

During the check required by paragraph (j) 

of this AD, if the bearing free-play is found 

to exceed the limits specified in Bombardier 

Service Bulletin 84–27–52, Revision A, dated 

March 5, 2012: Before further flight, replace 

the elevator PCU with a serviceable one, in 

accordance with paragraph 3.B., Part B, of 

Bombardier Service Bulletin 84–27–52, 

Revision A, dated March 5, 2012. 

(l) 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 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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(m) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2010–28R1, 

dated June 12, 2012, for related information, 

which can be found in the AD docket on the 

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

(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. 

(3) The following service information was 

approved for IBR on August 26, 2013. 

(i) Bombardier Service Bulletin 84–27–52, 

Revision A, dated March 5, 2012. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on August 1, 2011 (76 FR 

37253, June 27, 2011). 

(i) Bombardier Service Bulletin 84–27–52, 

dated May 25, 2010. 

(ii) Reserved. 

(5) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 

(6) 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. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

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

Issued in Renton, Washington, on June 21, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–17210 Filed 7–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0204; Directorate 

Identifier 2012–NM–229–AD; Amendment 

39–17510; AD 2013–14–05] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 747–400 

and 747–400F series airplanes. This AD 

was prompted by reports of cracking in 

the outboard flange of the longeron 

extension fittings, which attach to the 

wing-to-body fairing support frame. 

This AD requires repetitive inspections 

of the longeron extension fittings for 

cracking, and corrective actions if 

necessary. We are issuing this AD to 

detect and correct cracks in the longeron 

extension fittings, which can become 

large and adversely affect the structural 

integrity of the airplane. 

DATES: This AD is effective August 26, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of August 26, 2013. 

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 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. 


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43764 Federal Register / Vol. 78, No. 140 / Monday, July 22, 2013 / Rules and Regulations 

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, 

1601 Lind Avenue SW., Renton, 

Washington 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 include an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on March 7, 2013 (78 FR 

14731). The NPRM proposed to require 

repetitive inspections of the longeron 

extension fittings for cracking, and 

corrective actions if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 14731, 

March 7, 2013) and the FAA’s response 

to each comment. 

United Airlines (UAL) did not have 

any technical comments regarding the 

NPRM (78 FR 14731, March 7, 2013). 

Request to Change Applicability 

UPS and Virgin Atlantic Airways 

(VIR) stated that airplane line numbers 

1199 through 1419 inclusive are 

included in the effectivity of Boeing 

Alert Service Bulletin 747–53A2860, 

dated December 4, 2012, and that the 

applicability of the NPRM (78 FR 14731, 

March 7, 2013) includes airplane line 

numbers 1076 through 1419 inclusive. 

The commenters noted that Boeing Alert 

Service Bulletin 747–53A2860, dated 

December 4, 2012, does not provide 

inspection or repair instructions for 

airplanes with line numbers prior to 

1199. UPS requested that paragraph (c), 

‘‘Applicability,’’ in the NPRM be revised 

to match the effectivity included in the 

Boeing service information. We infer 

that VIR made the same request. 

Boeing requested that changes be 

made to paragraph (c), ‘‘Applicability,’’ 

and paragraph (i)(3), ‘‘Exceptions to 

Service Bulletin Specifications,’’ of the 

NPRM (78 FR 14731, March 7, 2013), in 

regard to the applicability. Boeing noted 

that line number 1076, included in 

paragraph (c), ‘‘Applicability,’’ does not 

align with any production line changes 

and the line numbers should be changed 

from 1076 through 1419 inclusive to 

1097 through 1419 inclusive. 

Boeing stated that paragraph (i)(3) of 

the NPRM (78 FR 14731, March 7, 2013) 

should be revised to clearly define the 

applicable airplanes because, as written, 

it could be interpreted to include more 

than the appropriate airplanes. Boeing 

requested that paragraph (i)(3) of the 

NPRM be revised to state ‘‘For airplanes 

not identified in Boeing Alert Service 

Bulletin 747–53A2860, dated December 

4, 2012, but are included in paragraph 

(c) of this AD: These airplanes are in 

Group 1 of the subject service bulletin 

for the purposes of this AD and are 

required to do the applicable actions 

specified in the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 747–53A2860, dated December 

4, 2012.’’ 

We agree with Boeing’s position 

regarding paragraphs (c) and (i)(3) of 

this final rule. We had conservatively 

established the applicability as starting 

at line number 1076 based on the 

information available at the time the 

NPRM (78 FR 14731, March 7, 2013) 

was issued. Since that time, Boeing has 

determined that the manufacturing 

change started at line number 1097. 

Boeing advised that Boeing Alert 

Service Bulletin 747–53A2860, dated 

December 4, 2012, will be revised and 

the effectivity in that service bulletin 

will be changed to start with line 

number 1097. Based on this 

information, we revised paragraph (c) in 

this final rule to include line numbers 

1097 through 1419 inclusive. We 

revised paragraph (i)(3) in this final rule 

to include text similar to that proposed 

by Boeing. 

We do not agree with UPS and VIR 

that the applicability of this final rule 

should match the effectivity in Boeing 

Alert Service Bulletin 747–53A2860, 

dated December 4, 2012. As stated 

previously, Boeing advised us that 

Boeing Alert Service Bulletin 747– 

53A2860, dated December 4, 2012, will 

be revised and the effectivity in the 

revised service bulletin will start with 

line number 1097. We have not changed 

this final rule in this regard. 

Request to Clarify the Difference in the 

Line Numbers Between the Service 

Information and the NPRM (78 FR 

14731, March 7, 2013) 

Boeing requested changes to the 

Discussion section of the NPRM (78 FR 

14731, March 7, 2013) to clarify the 

differences between the airplane line 

numbers (1199 through 1419 inclusive) 

identified in Boeing Alert Service 

Bulletin 747–53A2860, dated December 

4, 2012, and the airplane line numbers 

(1076 through 1419 inclusive) identified 

in paragraph (c) of the NPRM (78 FR 

14731, March 7, 2013). Boeing stated 

that, after the release of Boeing Alert 

Service Bulletin 747–53A2860, dated 

December 4, 2012, a crack was reported 

on airplane line number 1101 and that 

the longeron extension fitting had been 

redesigned at line number 1097. 

Boeing suggested that the text ‘‘. . . 

Subsequent analysis by Boeing 

indicated that the cracks were caused by 

fatigue combined with preload stress 

from improper fit-up during assembly. 

A manufacturing process change that 

began at line number 1199 might have 

resulted in preloading the longeron 

extension fittings . . .’’ be changed to 

‘‘Subsequent review by Boeing has 

shown that the reported cracking 

correlates with this design change made 

at line number 1097.’’ 

We agree that the suggestions made by 

Boeing provide a more accurate 

description of how the affected line 

numbers were determined; however, 

this information is not restated in the 

Discussion section of this final rule, so 

no change is needed. The line numbers 

were changed from 1076 through 1419 

inclusive to 1097 through 1419 

inclusive in paragraph (c), 

‘‘Applicability,’’ of this final rule, as 

explained previously. 

Concern Regarding Parts Availability 

UAL stated that Boeing Alert Service 

Bulletin 747–53A2860, dated December 

4, 2012, does not include price and 

supply data for replacement longeron 

fittings. UAL asked if operators are 

expected to fabricate these replacement 

fittings. UAL noted that, if operators do 

not have the capabilities to fabricate 

fittings, it could be difficult for those 

operators to get parts. 

We acknowledge the commenter’s 

concern regarding the availability of 

replacement longeron fittings. Boeing 

Alert Service Bulletin 747–53A2860, 

dated December 4, 2012, lists other 

available options as alternatives to 

replacing longeron extension fittings. 

The availability of required parts was 

considered when developing the 

compliance time for this AD. We have 


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Federal Register / Vol. 78, No. 140 / Monday, July 22, 2013 / Rules and Regulations 43765 

contacted Boeing regarding parts 

availability and Boeing responded that 

parts are available. Longeron extension 

fittings are a one piece forging and 

operators are not expected to fabricate 

these fittings. We have not changed this 

final rule in this regard. 

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 

14731, March 7, 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 14731, 

March 7, 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 41 

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 

High frequency eddy current inspection for 

cracking in longeron extension fittings.

32 work-hours × $85 per 

hour = $2,720, per inspection cycle.

$0 $2,720 $111,520, per inspection cycle. 

Option to do preventative modification instead of repetitive inspections.479 work-hours × $85 per 

hour = $40,715.

0 40,715 $1,669,315. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need this replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement .... 464 work-hours × $85 per hour = $39,440 .............................................................................. $0 $39,440 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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 

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 adding 

the following new airworthiness 

directive (AD): 

2013–14–05 The Boeing Company: 

Amendment 39–17510; Docket No. 

FAA–2013–0204; Directorate Identifier 

2012–NM–229–AD. 

(a) Effective Date 

This AD is effective August 26, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–400 and 747–400F series 

airplanes, certificated in any category, line 

numbers 1097 through 1419 inclusive. 


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(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking in the outboard flange of the 

longeron extension fittings, which attach to 

the wing-to-body fairing support frame. We 

are issuing this AD to detect and correct 

cracks in the longeron extension fittings, 

which can become large and adversely affect 

the structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection of Longeron Extension Fitting 

For all airplanes: Except as required by 

paragraphs (i)(1) and (i)(4) of this AD, at the 

time specified in table 1 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2860, dated December 4, 

2012, do a surface high frequency eddy 

current (HFEC) inspection of the left and 

right longeron extension fittings for cracking, 

and do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2860, dated December 4, 2012, 

except as required by paragraphs (i)(2) and 

(i)(3) of this AD. Do all applicable corrective 

actions before further flight. If no cracking is 

found, repeat the inspection thereafter at the 

intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2860, dated December 4, 

2012, until a permanent repair, longeron 

extension fitting replacement, or preventative 

modification is done, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2860, dated 

December 4, 2012. 

(h) Inspection of Temporary Repair and 

Corrective Actions 

For airplanes on which a temporary repair 

as specified in Boeing Alert Service Bulletin 

747–53A2860 has been done: At the times 

specified in table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2860, dated December 4, 

2012, do a surface HFEC inspection of the 

temporary repair of the longeron extension 

fittings for cracking, and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2860, dated 

December 4, 2012, except as required by 

paragraph (i)(3) of this AD. Do all applicable 

corrective actions before further flight. 

(i) Exceptions to Service Information 

(1) Where Boeing Alert Service Bulletin 

747–53A2860, dated December 4, 2012, 

specifies a compliance time relative to the 

issue date of that service bulletin, this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where Boeing Alert Service Bulletin 

747–53A2860, dated December 4, 2012, 

specifies to contact Boeing for repair 

information: Before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (k) of 

this AD. 

(3) For airplanes not identified in Boeing 

Alert Service Bulletin 747–53A2860, dated 

December 4, 2012, but included in paragraph 

(c) of this AD: These airplanes are in Group 

1 for the purposes of this AD. This AD 

requires that the applicable actions specified 

in the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2860, 

dated December 4, 2012, be accomplished on 

these airplanes. 

(4) Where Boeing Alert Service Bulletin 

747–53A2860, dated December 4, 2012, 

specifies ‘‘all airplanes,’’ this means all 

airplanes identified in paragraph (c) of this 

AD. 

(j) Optional Terminating Action 

Doing the permanent repair, longeron 

extension fitting replacement, or preventative 

modification, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2860, dated 

December 4, 2012, terminates the repetitive 

inspections required by paragraph (g) of this 

AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 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 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. 

(l) Related Information 

For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, Washington 

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

917–6590; email: 

Nathan.P.Weigand@faa.gov. 

(m) 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 Alert Service Bulletin 747– 

53A2860, dated December 4, 2012. 

(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 the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

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

Issued in Renton, Washington, on June 25, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Manager, Transport 

Airplane Directorate, Aircraft Certification 

Service. 

[FR Doc. 2013–17137 Filed 7–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0206; Directorate 

Identifier 2012–NM–068–AD; Amendment 

39–17507; AD 2013–14–02] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 727 airplanes. 

This AD was prompted by reports of 

spanwise cracks and corrosion in the 

wing center box upper skin and rear 

spar upper chord between left buttock 

line (LBL) 70.50 and right buttock line 

(RBL) 70.50 at body station (STA) 870. 

This AD requires repetitive inspections 

of the wing center box for cracking 

around certain fastener rows on the rear 

spar upper chord horizontal flange; for 

certain airplanes, repetitive inspections 

for cracking of the rear spar upper chord 

radius; for certain other airplanes, 

repetitive inspections for damage, 

cracking, and corrosion of the pressure 


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