44832 Federal Register / Vol. 80, No. 144 / Tuesday, July 28, 2015 / Rules and Regulations 

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

searching for and locating Docket No. FAA– 

2015–2463. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (k)(4) and (k)(6) of this AD. 

(k) 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 this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on July 14, 2015 (80 FR 

32449, June 9, 2015). 

(i) Bombardier Service Bulletin 84–29–34, 

dated May 9, 2013. 

(ii) Parker Service Bulletin 82910012–29– 

431, dated October 22, 2012. 

(4) For Bombardier 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. 

(5) For Parker service information 

identified in this AD, contact Parker 

Aerospace, 14300 Alton Parkway, Irvine, CA 

92618; phone: 949–833–3000; Internet: 

http://www.parker.com. 

(6) 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. 

(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 July 13, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–17975 Filed 7–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0778; Directorate 

Identifier 2014–NM–095–AD; Amendment 

39–18220; AD 2015–15–11] 

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 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747–400, 747– 

400D, 747–400F, 747SR, and 747SP 

series airplanes. This AD was prompted 

by reports of skin cracks and subsequent 

findings of hidden corrosion found on 

the mating surfaces between certain skin 

and stringers at circumferential skin 

splices. This AD requires general visual 

inspections of the fuselage skin at 

certain lower circumferential splices for 

the presence of existing external 

doublers, repetitive inspections of the 

fuselage skin, and related investigative 

and corrective actions if necessary. We 

are issuing this AD to detect and correct 

hidden corrosion due to compromised 

fillet seals, which can result in skin 

cracking and consequent loss of 

capability to support limit loads. 

DATES: This AD is effective September 1, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 1, 2015. 

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 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. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2014–0778. 

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– 

0778; 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 

Docket 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: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6432; fax: 425– 

917–6590; email: bill.ashforth@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 747–100B, 747–100B SUD, 747– 

200B, 747–200C, 747–200F, 747–300, 

747–400, 747–400D, 747–400F, 747SR, 

and 747SP series airplanes. The NPRM 

published in the Federal Register on 

November 28, 2014 (79 FR 70799). The 

NPRM was prompted by reports of skin 

cracks and subsequent findings of 

hidden corrosion found on the mating 

surfaces between certain skin and 

stringers at circumferential skin splices. 

The NPRM proposed to require general 

visual inspections of the fuselage skin at 

certain lower circumferential splices for 

the presence of existing external 

doublers, repetitive inspections of the 

fuselage skin, and related investigative 

and corrective actions if necessary. We 

are issuing this AD to detect and correct 

hidden corrosion due to compromised 

fillet seals, which can result in skin 

cracking and consequent loss of 

capability to support limit loads. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 70799, 

November 28, 2014) and the FAA’s 

response to each comment. 

Concurrence With NPRM (79 FR 70799, 

November 28, 2014) 

United Airlines stated that it concurs 

with the proposed requirements 

specified in the NPRM (79 FR 70799, 

November 28, 2014). 


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Federal Register / Vol. 80, No. 144 / Tuesday, July 28, 2015 / Rules and Regulations 44833 

Request To Clarify What Prompted the 

AD Action and Clarify the Unsafe 

Condition 

Boeing requested that we clarify the 

unsafe condition and revise various 

locations of the NPRM (79 FR 70799, 

November 28, 2014) to indicate that 

corrosion was discovered only after a 

skin crack was reported. Boeing 

explained the hidden corrosion between 

the skin and stringer was not visibly 

detectable and was discovered only after 

a skin crack was reported. 

We agree to revise the sentences that 

specify the unsafe condition and that 

specify what prompted the AD action. 

We have revised the SUMMARY of this 

final rule, as well as the Discussion and 

paragraph (e) of this AD, by adding the 

phrase ‘‘hidden corrosion due to’’ to the 

sentences that specify the unsafe 

condition, and by adding the phrase 

‘‘skin cracks and subsequent findings of 

hidden’’ to the sentences that discuss 

what prompted the AD action. 

Request To Clarify Requirements Based 

on Presence of Doubler Repair 

Boeing requested that we revise 

paragraph (g) of the NPRM (79 FR 

70799, November 28, 2014) to clarify the 

proposed requirements for surface low 

frequency eddy current (LFEC) 

inspections for areas with and without 

repair doublers. 

We agree to revise paragraph (g) of 

this AD to clarify configurations of areas 

with and without repair doublers. We 

have revised paragraph (g)(1) and added 

new paragraph (g)(2) to this AD to 

specify configurations having ‘‘an 

external repair doubler’’ and where ‘‘no 

existing repair doubler’’ exists. 

Request To Add Required High 

Frequency Eddy Current (HFEC) 

Inspections 

Boeing requested that we revise 

paragraphs (g)(2) and (h)(2)(i) of the 

NPRM (79 FR 70799, November 28, 

2014) by adding HFEC inspections as a 

required action. 

We disagree with specifying HFEC 

inspections as requested in this AD 

because this AD already requires 

compliance with all applicable ‘‘related 

investigative actions,’’ which include 

applicable HFEC inspections. The 

terminology for the proposed AD 

requirements was addressed by the 

NPRM (79 FR 70799, November 28, 

2014). Our standard practice is to 

specify actions that are related to the 

primary action and actions that further 

investigate the nature of any condition 

found as ‘‘related investigative actions.’’ 

No change has been made to this AD in 

this regard. 

Request To Reference Correct Service 

Information 

UPS requested that the correct eddy 

current inspection procedure be 

referenced in the NPRM (79 FR 70799, 

November 28, 2014). UPS stated that 

Boeing Information Notice 747– 

53A2861 IN 01, dated April 24, 2014, 

was issued to inform operators that 

Paragraph 3.B, Part 2, Step 1, of the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2861, 

dated April 1, 2014, should refer to ‘‘747 

Nondestructive test (NDT) Manual Part 

6, 53–30–00, Procedure 5,’’ instead of 

‘‘747 NDT Manual Part 6, 51–00–00, 

Procedure 8,’’ as the correct inspection 

procedure of the fuselage skin. UPS 

stated that adding this information 

would prevent the need for requests for 

alternative methods of compliance 

(AMOCs) related to this error. 

We find that clarification is needed. 

To clarify this information, we have 

added a new exception to include the 

correct source of service information for 

this inspection. New paragraph (i)(3) of 

this AD refers to ‘‘747 NDT Manual Part 

6, 53–30–00, Procedure 5,’’ as the 

appropriate source of service 

information for the eddy current 

inspection of the fuselage skin. We have 

also added a reference to paragraph 

(i)(3) of this AD in paragraphs (g) and 

(h) of this AD. 

Request To Exclude Location From 

Required Inspections 

UPS requested that the NPRM (79 FR 

70799, November 28, 2014) be revised to 

exclude a certain location from the 

inspection requirements, or that the 

proposed AD provide an inspection 

procedure that is adequate for that 

location. UPS stated that Boeing Alert 

Service Bulletin 747–53A2861, dated 

April 1, 2014, specifies that external 

surface LFEC inspections for corrosion 

of the fuselage skin be done using ‘‘747 

NDT Manual Part 6, 51–00–00, 

Procedure 5 or Procedure 12,’’ which 

are appropriate for skins with a 

specified thickness. UPS stated Table 2 

of Appendix C of Boeing Alert Service 

Bulletin 747–53A2861, dated April 1, 

2014, contains an error. Skin panels 

having part number 65B23792–XX are 

chem milled with a thickness that 

exceeds the specification listed in Table 

2 of Appendix C of Boeing Alert Service 

Bulletin 747–53A2861, dated April 1, 

2014. Therefore, the NDT procedures 

are not valid for those skin panels at this 

location. UPS stated that since action is 

identified as ‘‘Required for 

Compliance,’’ by Boeing Alert Service 

Bulletin 747–53A2861, dated April 1, 

2014, no deviations are allowed without 

AMOC approval. 

We disagree with the request. 

Agreeing with the request would delay 

the issuance of the AD and we find that 

delaying this action would be 

inappropriate in light of the identified 

unsafe condition. Boeing is aware of the 

discrepancy with the NDI instructions, 

and is actively working on a global 

AMOC for operators to correct the error 

by means of a validated procedure. 

Operators have the option of proposing 

their own procedure in accordance with 

paragraph (j) of this AD. 

Since chem milling affects the ability 

to accomplish Boeing Alert Service 

Bulletin 747–53A2861, dated April 1, 

2014, and the corrective action is not 

clear in the service information, we 

have added an exception to new 

paragraph (i)(4) of this AD to specify 

where Paragraph 3.B, Part 3, Step 1, of 

the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747– 

53A2861, dated April 1, 2014, specifies 

doing external surface LFEC inspections 

in accordance with ‘‘747 NDT Manual 

Part 6, 51–00–00, Procedure 5 or 

Procedure 12,’’ and the skin panels are 

chem milled with a thickness that 

exceeds the specification listed in Table 

2 of Appendix C of Boeing Alert Service 

Bulletin 747–53A2861, dated April 1, 

2014, this AD requires using an AMOC 

per paragraph (j) of this AD. We have 

added a reference to paragraph (i)(4) of 

this AD in paragraphs (g) and (h) of this 

AD. Operators may request approval of 

an AMOC under the provisions of 

paragraph (j) of this AD, for procedures 

that would help them meet the NDT test 

requirements. 

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 (79 FR 

70799, November 28, 2014) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 70799, 

November 28, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 747–53A2861, dated April 1, 


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44834 Federal Register / Vol. 80, No. 144 / Tuesday, July 28, 2015 / Rules and Regulations 

2014. The service information describes 

procedures for inspections of the 

fuselage skin at certain lower 

circumferential splices for the presence 

of existing external doublers, 

inspections of the fuselage skin for 

cracking and corrosion, and corrective 

actions. This service information is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section of this final rule. 

Costs of Compliance 

We estimate that this AD affects 165 

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 

Inspection ............................... Up to 121 work-hours × $85 

per hour = $10,285.

$0 Up to $10,285 ........................ Up to $1,697,025. 

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 

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): 

2015–15–11 The Boeing Company: 

Amendment 39–18220; Docket No. 

FAA–2014–0778; Directorate Identifier 

2014–NM–095–AD. 

(a) Effective Date 

This AD is effective September 1, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100B, 747–100B SUD, 747–200B, 

747–200C, 747–200F, 747–300, 747–400, 

747–400D, 747–400F, 747SR, and 747SP 

series airplanes; certificated in any category, 

as identified in Boeing Alert Service Bulletin 

747–53A2861, dated April 1, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of skin 

cracks and subsequent findings of hidden 

corrosion found on the mating surfaces 

between certain skin and stringers at 

circumferential skin splices. We are issuing 

this AD to detect and correct hidden 

corrosion due to compromised fillet seals, 

which can result in skin cracking and 

consequent loss of capability to support limit 

loads. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections and Repair for Group 1 

Airplanes 

For airplanes identified as Group 1 in 

Boeing Alert Service Bulletin 747–53A2861, 

dated April 1, 2014: At the applicable times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2861, 

dated April 1, 2014, except as provided by 

paragraph (i)(1) of this AD, do external 

general visual inspections for the presence of 

external doublers on the fuselage skin, and 

do the applicable actions specified in 

paragraphs (g)(1) and (g)(2) of this AD, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2861, dated April 1, 2014, except as 

required by paragraphs (i)(2), (i)(3), and (i)(4) 

of this AD. Do all applicable repetitive 

inspections of the fuselage skin thereafter at 

the applicable times specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2861, dated April 1, 2014. 

(1) For each affected area with an external 

repair doubler: Before further flight, do a 

surface low frequency eddy current (LFEC) 

inspection for skin cracks of the external 

lower lobe repair doubler, and do all 

applicable related investigative and 

corrective actions. Do all applicable related 

investigative and corrective actions before 

further flight. 

(2) For any affected area with no external 

repair doubler: Before further flight, do a 

surface LFEC inspection for corrosion of the 

external lower lobe skin surface, and do all 

applicable related investigative and 

corrective actions. Do all applicable related 

investigative and corrective actions before 

further flight. 

(h) Inspections and Repair for Group 2 

Airplanes 

For airplanes identified as Group 2 in 

Boeing Alert Service Bulletin 747–53A2861, 

dated April 1, 2014: At the applicable times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2861, 

dated April 1, 2014, except as provided by 

paragraph (i)(1) of this AD, do external 

general visual inspections for the presence of 


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Federal Register / Vol. 80, No. 144 / Tuesday, July 28, 2015 / Rules and Regulations 44835 

external doublers on the fuselage skin, and 

do the applicable actions specified in 

paragraphs (h)(1) and (h)(2) of this AD, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2861, dated April 1, 2014, except as 

required by paragraphs (i)(2), (i)(3), and (i)(4) 

of this AD. 

(1) For affected areas with any existing 

repair doubler: Before further flight, do 

inspections and applicable repairs using a 

method approved in accordance with the 

procedures specified by paragraph (j) of this 

AD. 

(2) For affected areas with no existing 

repair doubler, do the applicable actions 

specified in paragraph (h)(2)(i) and (h)(2)(ii) 

of this AD. 

(i) Before further flight, do a surface LFEC 

inspection for corrosion of the external lower 

lobe doubler, a surface LFEC inspection for 

skin cracks of the external lower lobe 

doubler, a detailed inspection for cracks of 

the external lower lobe skin, and do all 

applicable related investigative and 

corrective actions. Do all applicable related 

investigative and corrective actions before 

further flight. 

(ii) Do all applicable repetitive inspections 

of the fuselage skin thereafter at the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2861, dated April 1, 2014. 

(i) Exceptions to Service Information 

Specifications 

(1) Where Boeing Alert Service Bulletin 

747–53A2861, dated April 1, 2014, specifies 

a compliance time ‘‘after the original issue 

date of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Although Boeing Alert Service Bulletin 

747–53A2861, dated April 1, 2014, specifies 

to contact Boeing for repair data, and 

specifies that action as ‘‘RC’’ (Required for 

Compliance), this AD requires repair before 

further flight using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(3) Where Paragraph 3.B, Part 2, Step 1, of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2861, dated 

April 1, 2014, incorrectly identifies ‘‘747 

NDT Manual Part 6, 51–00–00, Procedure 8,’’ 

associated with the LFEC inspection for skin 

cracks of the external lower lobe repair 

doubler, the correct reference is ‘‘747 NDT 

Manual Part 6, 53–30–00, Procedure 5.’’ 

(4) Where Paragraph 3.B, Part 3, Step 1, of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2861, dated 

April 1, 2014, specifies doing external 

surface LFEC inspections in accordance with 

‘‘747 NDT Manual Part 6, 51–00–00, 

Procedure 5 or Procedure 12,’’ and the skin 

panels are chem milled with a thickness that 

exceeds the specification listed in Table 2 of 

Appendix C of Boeing Alert Service Bulletin 

747–53A2861, dated April 1, 2014, this AD 

requires using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(j) 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 (k) 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) Except as required by paragraph (i) of 

this AD: Some steps in the Work Instructions 

are labeled as Required for Compliance (RC). 

If this service bulletin is mandated by an AD, 

then the steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. Steps not 

labeled as RC may be deviated from using 

accepted methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of an 

AMOC, provided the RC steps, including 

substeps and identified figures, can still be 

done as specified, and the airplane can be 

put back in an airworthy condition. 

(4) 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. 

(k) Related Information 

For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6432; fax: 425–917–6590; 

email: bill.ashforth@faa.gov. 

(l) 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– 

53A2861, dated April 1, 2014. 

(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, 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 July 16, 

2015. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–18156 Filed 7–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0921; Directorate 

Identifier 2014–NM–073–AD; Amendment 

39–18193; AD 2015–13–06] 

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) 2013–14– 

05 for certain The Boeing Company 

Model 747–400 and 747–400F series 

airplanes. AD 2013–14–05 required 

repetitive inspections of the longeron 

extension fittings for cracking, and 

related investigative and corrective 

actions if necessary. This new AD 

would continue to require the actions 

specified in AD 2013–14–05, and would 

add new repetitive high frequency eddy 

current (HFEC) inspections of any 

modified, repaired, or replaced longeron 

extension fitting for cracking, and 

applicable related investigative and 

corrective actions if necessary. This AD 

was prompted by reports of cracking in 

the outboard flange of the longeron 

extension fittings, and our 

determination that more work is 

necessary on airplanes on which a 

permanent repair, longeron extension 

fitting replacement, or modification was 

accomplished. 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 September 1, 

2015. 


asabaliauskas on DSK5VPTVN1PROD with RULES