26606 Federal Register / Vol. 79, No. 90 / Friday, May 9, 2014 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0686; Directorate 

Identifier 2013–NM–006–AD; Amendment 

39–17843; AD 2014–09–08] 

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) 2007–16– 

19, which applied to certain The Boeing 

Company Model 747–200B, 747–300, 

and 747–400 series airplanes. AD 2007– 

16–19 required repetitive detailed 

inspections for cracking of the aft 

tension tie channels from body station 

(BS) 1120 to BS 1220 and from BS 880 

to BS 1100, and corrective actions if 

necessary. AD 2007–16–19 also 

provided optional terminating action. 

This new AD retains the existing 

requirements, limits the area of the 

detailed inspection, adds repetitive 

surface high-frequency eddy current 

inspections, and mandates the 

previously optional terminating action. 

This AD was prompted by an analysis 

that indicated the need to mandate the 

previously optional modification. We 

are issuing this AD to prevent fatigue 

cracking of the tension ties, which could 

result in reduced structural integrity of 

the airplane and rapid depressurization 

of the airplane. 

DATES: This AD is effective June 13, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 13, 2014 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of September 12, 2012 (77 FR 

47267, August 8, 2012). 

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. 

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–2013– 

0686; 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 to supersede AD 2007–16–19, 

Amendment 39–15158 (72 FR 45151, 

August 13, 2007). AD 2007–16–19 

applied to certain The Boeing Company 

Model 747–200B, 747–300, and 747–400 

series airplanes. The NPRM published 

in the Federal Register on August 12, 

2013 (78 FR 48835). The NPRM was 

prompted by an analysis that indicated 

the need to mandate the previously 

optional modification. The NPRM 

proposed to continue to require 

repetitive detailed inspections for 

cracking of the aft tension tie channels 

from body station (BS) 1120 to BS 1220 

and from BS 880 to BS 1100, and 

corrective actions if necessary. The 

NPRM also proposed to provide 

optional terminating action for the 

repetitive detailed inspections at BS 

1120 to 1220. The NPRM also proposed 

to limit the area of the detailed 

inspection, add repetitive surface highfrequency eddy current inspections, and 

mandate the previously optional 

terminating action for BS 880 to 1100. 

We are issuing this AD to prevent 

fatigue cracking of the tension ties, 

which could result in reduced structural 

integrity of the airplane and rapid 

depressurization of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 48835, 

August 12, 2013) and the FAA’s 

response to each comment. 

Request To Change Service Information 

Reference 

Paragraph (h) of the NPRM (78 FR 

48835, August 12, 2013) specified a 

modification and related investigative 

and corrective actions, in accordance 

with Boeing Alert Service Bulletin 747– 

53A2610, Revision 1, dated December 4, 

2012. Paragraph (h) of the NPRM 

included the following provision: 

Modification of a tension tie at STA 1120 

to 1220, as required by paragraph (p) of AD 

2012–15–13 . . ., is acceptable for 

compliance with the requirements of 

paragraph (h) of this AD for that tension tie 

location only. 

Boeing requested that we revise that 

sentence to specify that the modification 

is terminating action if done in 

accordance with Boeing Service Bulletin 

747–53A2559, Revision 1, dated August 

4, 2011—instead of AD 2012–15–13, 

Amendment 39–17142 (77 FR 47267, 

August 8, 2012), which could be 

superseded in the future. 

We agree with the request, for the 

reasons provided by the commenter, 

and have revised this terminating action 

provision accordingly in this final rule. 

We have also revised paragraph (b) of 

this final rule to remove the reference to 

AD 2012–15–13, Amendment 39–17142 

(77 FR 47267, August 8, 2012). In 

addition, we have moved the 

terminating action provisions from 

paragraph (h) of this final rule to a new 

paragraph (i) in this final rule, and 

redesignated subsequent paragraphs 

accordingly. 

Requests for More Specific Exception 

References 

Boeing requested that we revise 

paragraphs (g) and (h) of the NPRM (78 

FR 48835, August 12, 2013) to change 

the reference to the compliance-time 

exception paragraph, which the NPRM 

identified as paragraph ‘‘(i).’’ Boeing 

requested that we more specifically 

identify this exception as paragraph 

‘‘(i)(2)’’ of the NPRM. 

We agree, and have revised 

paragraphs (g) and (h) accordingly in 

this final rule—except that paragraph 

(i)(2) of the NPRM (78 FR 48835, August 

12, 2013) has been redesignated as 

paragraph (j)(2) in this final rule. 

Additional Changes to NPRM (78 FR 

48835, August 12, 2013) 

Paragraph (h) of the NPRM (78 FR 

48835, August 12, 2013) provided 

terminating action for all tension tie 

locations (BS 880 to 1220). We have 

revised paragraph (h) in this final rule 

to require terminating action for BS 880 


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Federal Register / Vol. 79, No. 90 / Friday, May 9, 2014 / Rules and Regulations 26607 

to 1100 only, and to move the (optional) 

terminating action for BS 1120 to 1220 

to new paragraph (i) in this final rule. 

We redesignated subsequent paragraphs 

accordingly. 

We have further revised paragraph (h) 

of the NPRM (78 FR 48835, August 12, 

2013), now paragraphs (h) and (i) in this 

final rule, to clarify that modification of 

a tension tie is acceptable for 

compliance with the requirements of 

paragraph (g) of this AD for the affected 

tension tie location only. 

Paragraph (h) of the NPRM (78 FR 

48835, August 12, 2013) incorrectly 

stated that it terminated paragraph (h) of 

the AD. Paragraphs (h) and (i) in this 

final rule instead identify paragraph (g) 

of the AD as the terminated action. 

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 

48835, August 12, 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 48835, 

August 12, 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 1 

airplane 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 

Retained detailed inspection (retained actions).4 work-hours × $85 per hour = 

$340 per inspection cycle.

$0 $340 per inspection 

cycle.

$340 per inspection 

cycle. 

New surface high-frequency eddy 

current inspection.

4 work-hours × $85 per hour = 

$340 per inspection cycle.

0 $340 per inspection 

cycle.

$340 per inspection 

cycle. 

New modification .............................. 64 work-hours × $85 per hour = 

$5,440.

14,948 $20,388 ........................ $20,388 

We have received no definitive data 

that would enable us to provide workhour estimates for repair of cracks found 

in a bolt hole during the detailed 

inspection specified in this AD. The 

cost for parts (oversized fastener kit) for 

this condition is $2,292. 

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) 

2007–16–19, Amendment 39–15158 (72 

FR 45151, August 13, 2007), and adding 

the following new AD: 

2014–09–08 The Boeing Company: 

Amendment 39–17843; Docket No. 

FAA–2013–0686; Directorate Identifier 

2013–NM–006–AD. 

(a) Effective Date 

This AD is effective June 13, 2014. 

(b) Affected ADs 

This AD supersedes AD 2007–16–19, 

Amendment 39–15158 (72 FR 45151, August 

13, 2007). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–200B, 747–300, and 747–400 

series airplanes, certificated in any category, 

as identified in Boeing Alert Service Bulletin 

747–53A2610, Revision 1, dated December 4, 

2012. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder (DAH) indicating 

that the tension ties are subject to widespread 

fatigue damage (WFD). We are issuing this 

AD to prevent fatigue cracking of the tension 

ties, which could result in reduced structural 

integrity of the airplane and rapid 

depressurization of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2610, 

Revision 1, dated December 4, 2012, except 

as specified in paragraph (j)(2) of this AD: Do 


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26608 Federal Register / Vol. 79, No. 90 / Friday, May 9, 2014 / Rules and Regulations 

detailed and surface high-frequency eddy 

current inspections for cracks in the tension 

ties at body station (BS) 880 to 1100, 1120, 

1160, 1200, and 1220, and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2610, Revision 1, 

dated December 4, 2012, except as required 

by paragraph (j)(3) of this AD. Do all 

applicable corrective actions before further 

flight. Repeat the inspections thereafter at the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2610, Revision 1, dated 

December 4, 2012, until the tension ties have 

been modified as required by paragraph (h) 

of this AD or as specified in paragraph (i) of 

this AD. Repair or modification of a tension 

tie at any location in accordance with Part 3 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2610, 

Revision 1, dated December 4, 2012, 

terminates the repetitive inspection 

requirements of this AD for that tension tie 

location only. 

(h) Tension Tie Modification: BS 880 to 1100 

At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2610, 

Revision 1, dated December 4, 2012, except 

as specified in paragraph (j)(2) of this AD: 

Modify the tension ties from BS 880 to 1100, 

and do all applicable related investigative 

and corrective actions, in accordance with 

Part 3 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2610, 

Revision 1, dated December 4, 2012, except 

as required by paragraph (j)(3) of this AD. Do 

all applicable related investigative and 

corrective actions before further flight. 

Modification as required by this paragraph 

terminates the repetitive inspection 

requirements of paragraph (g) of this AD for 

the affected tension tie location(s) only. 

(i) Optional Terminating Action: BS 1120 to 

1220 

Modification of a tension tie at BS 1120 to 

1220 in accordance with Boeing Service 

Bulletin 747–53A2559, Revision 1, dated 

August 4, 2011, except as required by 

paragraph (j)(4) of this AD, terminates the 

requirements of paragraph (g) of this AD for 

that tension tie location only. Paragraph (p) 

of AD 2012–15–13, Amendment 39–17142 

(77 FR 47267, August 8, 2012), mandates the 

accomplishment of the modification and 

associated actions specified in Boeing 

Service Bulletin 747–53A2559, Revision 1, 

dated August 4, 2011. 

(j) Service Information Clarification and 

Exceptions 

(1) Paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2610, 

Revision 1, dated December 4, 2012, specifies 

certain compliance times ‘‘after August 28, 

2007.’’ August 28, 2007, is the effective date 

of AD 2007–16–19, Amendment 39–15158 

(72 FR 45151, August 13, 2007). 

(2) Where Boeing Alert Service Bulletin 

747–53A2610, Revision 1, dated December 4, 

2012, specifies a compliance time ‘‘after the 

Revision 1 date of this service bulletin,’’ this 

AD requires compliance within the specified 

time after the effective date of this AD. 

(3) Where Boeing Alert Service Bulletin 

747–53A2610, Revision 1, dated December 4, 

2012, specifies to contact Boeing for certain 

repair instructions: Repair before further 

flight using a method approved in 

accordance with the procedures specified in 

paragraph (l) of this AD. 

(4) Where Boeing Service Bulletin 747– 

53A2559, Revision 1, dated August 4, 2011, 

specifies to contact Boeing for repair 

instructions or additional modification 

requirements, repair of the cracking or 

additional actions must be done using a 

method approved in accordance with the 

procedures specified in paragraph (l) of this 

AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

detailed inspections, repairs, and 

modification specified in paragraphs (g) and 

(h) of this AD, for that affected tension tie 

location only, if those actions were 

performed before the effective date of this AD 

using Boeing Alert Service Bulletin 747– 

53A2610, dated May 10, 2007 (which is not 

incorporated by reference in this AD). 

(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)(1) 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. 

(4) AMOCs approved previously in 

accordance with AD 2007–16–19, 

Amendment 39–15158 (72 FR 45151, August 

13, 2007), are approved as AMOCs for the 

corresponding provisions of this AD. 

(m) Related Information 

(1) 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. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

paragraphs (n)(4) and (n)(5) 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. 

(3) The following service information was 

approved for IBR on June 13, 2014. 

(i) Boeing Alert Service Bulletin 747– 

53A2610, Revision 1, dated December 4, 

2012. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on September 12, 2012 (77 

FR 47267, August 8, 2012). 

(i) Boeing Service Bulletin 747–53A2559, 

Revision 1, dated August 4, 2011. 

(ii) Reserved. 

(5) 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. 

(6) You may view this service information 

at FAA, 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 April 22, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–09832 Filed 5–8–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0130; Directorate 

Identifier 2014–CE–005–AD; Amendment 

39–17847; AD 2014–09–12] 

RIN 2120–AA64 

Airworthiness Directives; Alpha 

Aviation Concept Limited Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Alpha Aviation Concept Limited Model 

R2160 airplanes. This AD results from 


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