Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations 72569 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (o)(5) and (o)(6) of this AD. 

(o) 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 December 28, 2015. 

(i) Lockheed Service Bulletin 382–57–85 

(82–790), Revision 3, dated July 8, 2013, 

including Appendix A, Revision 3, dated July 

8, 2013, and Appendixes B, C, D, E, F, and 

G, all Revision 1, all dated March 8, 2007. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on June 22, 2011 (76 FR 

28626, May 18, 2011). 

(i) Lockheed Service Bulletin 382–57–85 

(82–790), Revision 2, dated August 23, 2007, 

including Appendixes A, B, C, D, E, F, and 

G, all Revision 1, all dated March 8, 2007. 

(ii) Reserved. 

(5) For Lockheed Martin Corporation/

Lockheed Martin Aeronautics Company 

service information identified in this AD, 

contact Lockheed Martin Corporation/

Lockheed Martin Aeronautics Company, 

Airworthiness Office, Dept. 6A0M, Zone 

0252, Column P–58, 86 S. Cobb Drive, 

Marietta, GA 30063; telephone 770–494– 

5444; fax 770–494–5445; email ams.portal@

lmco.com; Internet http://

www.lockheedmartin.com/ams/tools/

TechPubs.html. 

(6) 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. 

(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 October 

29, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–28464 Filed 11–19–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–1043; Directorate 

Identifier 2013–NM–079–AD; Amendment 

39–18321; AD 2015–23–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A330–200, A330–200 

Freighter, and A330–300 series 

airplanes; and Model A340–200 and 

A340–300 series airplanes. This AD was 

prompted by reports of cracked support 

strut body ends at a certain frame 

location of the trimmable horizontal 

stabilizer (THS). This AD requires 

repetitive inspections for cracking of the 

strut ends of the THS support located at 

a certain frame in the tail cone, and 

replacement if necessary; and 

reinstallation or installation of 

reinforcing clamps on certain strut ends. 

We are issuing this AD to detect and 

correct cracked support strut body ends 

of the THS, which could lead to the loss 

of all four THS support struts, making 

the remaining structure unable to carry 

limit loads, resulting in the loss of the 

horizontal tail plane. 

DATES: This AD becomes effective 

December 28, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 28, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-1043 or in 

person at the 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. 

For service information identified in 

this AD, contact Airbus SAS, 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.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– 

1043. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

fax 425–227–1149. 

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 all Airbus Model A330–200, 

A330–200 Freighter, and A330–300 

series airplanes; and Model A340–200 

and A340–300 series airplanes. The 

NPRM published in the Federal 

Register on January 23, 2015 (80 FR 

3510). The NPRM was prompted by 

reports of cracked support strut body 

ends at a certain frame location of the 

THS. The NPRM proposed to require 

repetitive inspections for cracking of the 

strut ends of the THS support located at 

a certain frame in the tail cone, and 

replacement if necessary; and 

reinstallation or installation of 

reinforcing clamps on certain strut ends. 

We are issuing this AD to detect and 

correct cracked support strut body ends 

of the THS, which could lead to the loss 

of all four THS support struts, making 

the remaining structure unable to carry 

limit loads, resulting in the loss of the 

horizontal tail plane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0068, dated March 18, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for all Airbus 

Model A330–200, A330–200 Freighter, 

and A330–300 series airplanes; and 

Model A340–200 and A340–300 series 

airplanes. The MCAI states: 

During scheduled maintenance on A330 

aeroplanes, several Trimmable Horizontal 

Stabilizer (THS) support struts at frame (FR) 

91 were found cracked at strut body ends. 

The THS is supported and articulated at FR 

91 by four struts to fix the hinges (Y-bolts) 

and keep the structural integrity in lateral 

direction. 

Analysis revealed that cracks can reduce 

ability of the support struts to carry specified 

tension loads. 

This condition, if not detected and 

corrected, could lead to the loss of all four 


tkelley on DSK3SPTVN1PROD with RULES
72570 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations 

THS support struts at FR91, which would 

make the remaining structure unable to carry 

limit loads, resulting in the loss of Horizontal 

Tail Plane. 

A340–500/600 aeroplanes are not affected 

by this [EASA] AD as different material is 

used on THS support struts. 

To address this potentially unsafe 

condition, EASA issued AD 2013–0076 

[http://ad.easa.europa.eu/blob/easa_ad_

2013_0076_superseded.pdf/AD_2013-0076_

1] to require repetitive special detailed 

inspections [high frequency eddy current 

(HFEC) inspections for cracking] of all 8 strut 

ends of the THS support located at FR91 in 

the tail cone and, depending on findings, 

replacement of THS support struts. That 

[EASA] AD also required, for aeroplanes on 

which Airbus Modification 203493 had not 

been embodied in production, or Airbus 

Service Bulletin (SB) A330–53–3204 or SB 

A340–53–4199, as applicable, has not been 

embodied in service, the installation of a 

clamping device on each support strut end to 

stop growth of possible cracks (crack stopper 

function) in order to secure integrity of the 

struts. 

Since issuance of EASA AD 2013–0076 

[http://ad.easa.europa.eu/blob/easa_ad_

2013_0076_superseded.pdf/AD_2013-0076_

1], it has been discovered that several 

aeroplanes are fitted with another strut 

configuration (SARMA Strut) [Societe ́

Anonyme de Recherche Me ́canique 

Applique ́e] than the TAC (Technical 

Airborne Components Industries) strut, 

which caused the other strut not to be 

considered. Consequently, Airbus revised 

Airbus SB A330–53–3206 and SB A340–53– 

4208, accordingly in order to add a one-time 

[HFEC] inspection [for cracking] for SARMA 

struts and in case of finding to replace it with 

a TAC strut and thereafter to accomplish 

repetitive inspections and EASA issued AD 

2013–0219 [http://ad.easa.europa.eu/blob/

easa_ad_2013_0219_superseded.pdf/AD_

2013-0219_1], which is superseded, and 

required accomplishment of the instructions 

as specified in the latest revision of each SB, 

as applicable. 

Since issuance of EASA AD 2013–0219 

[http://ad.easa.europa.eu/blob/easa_ad_

2013_0219_superseded.pdf/AD_2013-0219_

1], based on the reporting received from 

operators, it has been determined that 

repetitive inspections are also to be 

accomplished for aeroplanes equipped with 

SARMA strut. Airbus introduced that 

inspection in the applicable SB at revision 3. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2013–0219, which is superseded, and 

requires accomplishment of repetitive 

[HFEC] inspective inspection [for cracking] 

for aeroplanes equipped with SARMA strut. 

This [EASA] AD is considered as an 

interim action, pending the development of 

a terminating action. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-1043- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (80 FR 3510, 

January 23, 2015) and the FAA’s 

response to each comment. 

Request To Add Inspection for 

Identifying Struts 

Delta Air Lines, Inc. (DAL) requested 

that we add a physical inspection to 

paragraph (g) of the proposed AD (80 FR 

3510, January 23, 2015) to distinguish a 

Societe ́ Anonyme de Recherche 

Me ́canique Applique ́e (SARMA) strut 

from a Technical Airborne Components 

Industries (TAC) strut. DAL stated that 

paragraph (g) of the proposed AD only 

identifies the dimensional diameter of 

SARMA struts; however, DAL stated 

that both TAC and SARMA struts have 

the same manufacturer part numbers but 

have different rod end diameters. DAL 

suggested language for doing a physical 

inspection of the strut end of each 

support strut for identification 

purposes. 

We agree that a physical inspection is 

necessary to determine the rod end 

diameter in order to distinguish 

between SARMA and TAC struts. 

However, that inspection is optional. 

Paragraph (g) of this AD defines SARMA 

struts as having a diameter that is less 

than 43 millimeters, and states that all 

other struts are TAC struts. Paragraph 

(h) of this AD requires inspecting TAC 

struts. Thus, operators must inspect all 

struts unless the strut is inspected to 

determine the diameter is less than 43 

millimeters, i.e., it is a SARMA strut. 

We have not changed this AD in this 

regard. 

Request To Include Airbus 

Modification 203834 for Installing 

Reinforced Clamps 

DAL requested that we revise 

paragraph (h) of the proposed AD (80 FR 

3510, January 23, 2015) to include 

Airbus Modification 203834 as an 

optional modification for installation of 

the reinforced clamps. DAL stated that 

Airbus has confirmed that Airbus 

Modification 203834 installs the same 

reinforced clamps as Airbus 

Modification 203493 specified in 

paragraph (h) of the proposed AD. 

We agree with the commenter’s 

request. The FAA has approved two 

Airbus modifications for installing the 

reinforced clamps into production 

airplanes: Modification 203493 for 

airplanes having manufacturer serial 

number (MSN) 1466 to 1509 inclusive, 

and Modification 203834 for airplanes 

having MSN 1510 and on. Modification 

203834 supersedes Modification 

203493, and the first airplane delivered 

with Modification 203834 installed was 

MSN 1511. 

Thus, operators may have the two 

populations of airplanes: Those with 

Modification 203834 and those with 

Modification 203493. This AD must 

address both groups of airplanes 

accordingly. We have revised paragraph 

(h) of this AD to specify that, for 

airplanes on which Airbus Modification 

203493 or 203834 has been embodied in 

production; or on which Airbus Service 

Bulletin A330–53–3204 or Airbus 

Service Bulletin A340 53–4199, as 

applicable; has been embodied in 

service, remove the clamp from each 

strut end before accomplishing the 

inspections required by paragraph (h) of 

this AD. 

Request To Include Additional Service 

Information 

DAL requested that we revise 

paragraphs (j)(1), (j)(2), and (l) of the 

proposed AD (80 FR 3510, January 23, 

2015) to include Airbus Service Bulletin 

A330–53–3204. DAL stated that, when 

clamps were not previously installed, 

Airbus Service Bulletin A330–53–3204 

becomes the source document for 

installing the clamps. 

We agree that Airbus Service Bulletin 

A330–53–3204, Revision 03, dated 

February 28, 2014, is an appropriate 

source of service information for 

installing clamps. However, we do not 

agree to revise this AD because that 

service information is already 

referenced in Airbus Service Bulletin 

A330–53–3206, Revision 03, dated 

February 28, 2014, which is referred to 

as one of the appropriate sources of 

service information for the actions 

required by paragraphs (j)(1), (j)(2), and 

(l) of this AD. As specified in the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3206, 

Revision 03, dated February 28, 2014., 

‘‘if no clamps were previously installed, 

accomplish Service Bulletin A330–53– 

3204 before next flight, to install them.’’ 

Therefore, no change to this AD is 

necessary in this regard. 

Request To Clarify Flight With 

Cracking 

DAL requested that we clarify/

confirm that the NPRM (80 FR 3510, 

January 23, 2015) will apply more strict 

replacement criteria when cracks are 

found than what is currently published 

in Airbus Service Bulletin A330–53– 

3206, Revision 03, dated February 28, 

2014. DAL stated that Subtask 533206– 

280–201–001 of Airbus Service Bulletin 

A330–53–3206, Revision 03, dated 

February 28, 2014, contains instructions 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations 72571 

to allow continued operation of the 

airplane with small crack findings 

without immediate strut replacement. 

We agree. In the ‘‘Differences Between 

this Proposed AD and the MCAI or 

Service Information’’ section of the 

NPRM (80 FR 3510, January 23, 2015), 

we stated that ‘‘Although EASA 

Airworthiness Directive 2014–0068, 

dated March 18, 2014, Airbus Service 

Bulletin A330–53–3206, Revision 03, 

dated February 28, 2014, and Airbus 

Service Bulletin A340–53–4208, 

Revision 03, dated February 28, 2014, 

allow further flight after certain cracks 

are found during compliance with the 

proposed action, paragraph (j)(2) of this 

AD would require that any cracked THS 

support strut be replaced with a new or 

serviceable TAC strut before further 

flight.’’ No change to this AD is 

necessary 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 (80 FR 3510, 

January 23, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 3510, 

January 23, 2015). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Interim Action 

We consider this AD interim action. If 

final action is later identified, we might 

consider further rulemaking then. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following service 

information. 

• Airbus Service Bulletin A330–53– 

3206, Revision 03, dated February 28, 

2014. This service information describes 

procedures for inspections for cracking 

of the strut ends of the THS support 

located in the airplane tail cone. 

• Airbus Service Bulletin A340–53– 

4208, Revision 03, dated February 28, 

2014. This service information describes 

procedures for inspections for cracking 

of the strut ends of the THS support 

located in the airplane tail cone. 

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 AD. 

Costs of Compliance 

We estimate that this AD affects 84 

airplanes of U.S. registry. 

We also estimate that it will take 

about 9 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $64,260, or $765 per 

product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition 

replacement specified in this AD. 

We estimate that any necessary 

follow-on strut reinforcements will take 

about 2 work-hours and require parts 

costing $5,680, for a cost of $5,850 per 

product. We have no way of 

determining the number of aircraft that 

might need this action. 

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 

We 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 the 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/#!docket

Detail;D=FAA-2014-1043; 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 

street address for the Docket Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. 

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): 

2015–23–05 Airbus: Amendment 39–18321. 

Docket No. FAA–2014–1043; Directorate 

Identifier 2013–NM–079–AD. 

(a) Effective Date 

This AD becomes effective December 28, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1), (c)(2), and (c)(3) of this 

AD, certificated in any category, all 

manufacturer serial numbers. 

(1) Airbus Model A330–201, –202, –203, 

–223, –223F, –243, and –243F airplanes. 


tkelley on DSK3SPTVN1PROD with RULES
72572 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations 

(2) Airbus Model A330–301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes. 

(3) Airbus Model A340–211, –212, –213, 

–311, –312, and –313 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of 

cracked support strut body ends at a certain 

frame location of the trimmable horizontal 

stabilizer (THS). We are issuing this AD to 

detect and correct cracked support strut body 

ends of the THS, which could lead to the loss 

of all four THS support struts and which 

would make the remaining structure unable 

to carry limit loads, resulting in the loss of 

the horizontal tail plane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definition of Strut Types 

For the purpose of this AD, a Societe ́

Anonyme de Recherche Me ́canique 

Applique ́e (SARMA) strut is a strut on which 

the diameter of the strut end is less than 43 

millimeters. All other struts are Technical 

Airborne Components Industries (TAC) 

struts. 

(h) Repetitive Inspections of TAC Strut Ends 

At the applicable time specified in 

paragraph (i) of this AD, do a high frequency 

eddy current (HFEC) inspection for cracking 

of all TAC strut ends of the THS support 

located at frame (FR) 91 in the tail cone, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

53–3206, Revision 03, dated February 28, 

2014; or Airbus Service Bulletin A340–53– 

4208, Revision 03, dated February 28, 2014; 

as applicable. Repeat the inspection 

thereafter at intervals not to exceed 42 

months or 20,000 flight hours, whichever 

occurs first. For airplanes on which Airbus 

Modification 203493 or 203834 has been 

embodied in production, or Airbus Service 

Bulletin A330–53–3204 or Airbus Service 

Bulletin A340–53–4199, as applicable, has 

been embodied in service, remove the clamp 

from each strut end before accomplishing the 

inspections required by this paragraph. 

(i) Compliance Times for the Actions 

Required by Paragraphs (h) and (k) of This 

AD 

Do the inspections required by paragraphs 

(h) and (k) of this AD at the applicable times 

specified in paragraphs (i)(1), (i)(2), and (i)(3) 

of this AD. 

(1) For Model A330 series airplanes having 

manufacturer serial numbers 012 through 209 

inclusive, and Model A340 series airplanes 

having manufacturer serial numbers 002 

through 210 inclusive: Within 6 months after 

the effective date of this AD. 

(2) For Model A330 series airplanes having 

manufacturer serial numbers 211 through 422 

inclusive, and Model A340 series airplanes 

having manufacturer serial numbers 212 

through 447 inclusive: Within 24 months 

after the effective date of this AD. 

(3) For Model A330 series airplanes having 

manufacturer serial numbers 423 and 

subsequent, and Model A340 series airplanes 

having manufacturer serial numbers 450 

through 955 inclusive: Within 36 months 

after the effective date of this AD or since the 

first flight of the airplane, whichever occurs 

later. 

(j) Corrective Action for TAC Strut Ends and 

Installation of Reinforcing Clamps 

(1) If, during any inspection required by 

paragraph (h) of this AD, no cracks are found: 

Before further flight, reinstall or install, as 

applicable, reinforcing clamps on the strut 

ends, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3206, Revision 03, 

dated February 28, 2014; or Airbus Service 

Bulletin A340–53–4208, Revision 03, dated 

February 28, 2014; as applicable. 

(2) If, during any inspection required by 

paragraph (h) of this AD, any crack is found: 

Before further flight, replace any affected 

strut with a new or serviceable TAC strut and 

install reinforcing clamps on the strut end, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

53–3206, Revision 03, dated February 28, 

2014; or Airbus Service Bulletin A340–53– 

4208, Revision 03, dated February 28, 2014; 

as applicable. 

(k) Repetitive Inspections of SARMA Strut 

Ends 

At the applicable time specified in 

paragraph (i) of this AD, do an HFEC 

inspection for cracking of all SARMA strut 

ends of the THS support located at FR 91 in 

the tail cone, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3206, Revision 03, 

dated February 28, 2014; or Airbus Service 

Bulletin A340–53–4208, Revision 03, dated 

February 28, 2014; as applicable. Repeat the 

inspection thereafter at intervals not to 

exceed 12 months. 

(l) Corrective Action for SARMA Strut Ends 

If any crack is found on a strut end during 

the inspection required by paragraph (k) of 

this AD: Before further flight, replace any 

affected SARMA strut with a new or 

serviceable TAC strut and install reinforcing 

clamps on the strut end, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3206, Revision 03, 

dated February 28, 2014; or Airbus Service 

Bulletin A340–53–4208, Revision 03, dated 

February 28, 2014; as applicable. 

(m) No Terminating Action 

Replacement of THS struts on an airplane 

does not constitute terminating action for the 

repetitive inspections required by this AD. 

(n) No Reporting 

Although Airbus Service Bulletin A330– 

53–3206, Revision 03, dated February 28, 

2014; and Airbus Service Bulletin A340–53– 

4208, Revision 03, dated February 28, 2014; 

specify to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(o) Credit for Previous Actions 

This paragraph provides credit for actions 

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

this AD, if those actions were performed 

before the effective date of this AD using any 

of the service information identified in 

paragraphs (n)(1) through (n)(6) of this AD. 

This service information is not incorporated 

by reference in this AD. 

(1) Airbus Service Bulletin A330–53–3206, 

dated February 7, 2013. 

(2) Airbus Service Bulletin A330–53–3206, 

Revision 01, dated June 10, 2013. 

(3) Airbus Service Bulletin A330–53–3206, 

Revision 02, dated August 8, 2013. 

(4) Airbus Service Bulletin A340–53–4208, 

dated February 7, 2013. 

(5) Airbus Service Bulletin A340–53–4208, 

Revision 01, dated June 10, 2013. 

(6) Airbus Service Bulletin A340–53–4208, 

Revision 02, dated August 8, 2013. 

(p) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0068, dated 

March 18, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

#!documentDetail;D=FAA-2014-1043-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(r) 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. 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations 72573 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A330–53–3206, 

Revision 03, dated February 28, 2014. 

(ii) Airbus Service Bulletin A340–53–4208, 

Revision 03, dated February 28, 2014. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.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 October 

30, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–28895 Filed 11–19–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1266; Directorate 

Identifier 2014–NM–151–AD; Amendment 

39–18327; AD 2015–23–11] 

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 747–100, 

747–100B, 747–100B SUD, 747–200B, 

747–300, 747SR, and 747SP series 

airplanes. This AD was prompted by an 

evaluation by the design approval 

holder (DAH) indicating that certain 

fuselage skin lap joints are subject to 

widespread fatigue damage (WFD). This 

AD requires repetitive post-modification 

inspections for cracking of the skin or 

internal doubler along the edge fastener 

rows of the modification, and repair if 

necessary. We are issuing this AD to 

detect and correct fatigue cracking in 

certain fuselage skin lap joints, which 

could result in rapid depressurization of 

the airplane. 

DATES: This AD is effective December 

28, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 28, 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–2015– 

1266. 

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–2015– 

1266; 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: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

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 by adding an AD that would 

apply to certain The Boeing Company 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–300, 747SR, and 

747SP series airplanes. The NPRM 

published in the Federal Register on 

May 5, 2015 (80 FR 25630). The NPRM 

was prompted by an evaluation by the 

DAH indicating that certain fuselage 

skin lap joints are subject to WFD. The 

NPRM proposed to require repetitive 

post-modification inspections for 

cracking of the skin or internal doubler 

along the edge fastener rows of the 

modification, and repair if necessary. 

We are issuing this AD to detect and 

correct fatigue cracking in certain 

fuselage skin lap joints, which could 

result in 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 NPRM (80 FR 25630, 

May 5, 2015) and the FAA’s response to 

each comment. 

Request To Remove Warranty 

Statement 

Boeing requested that we remove the 

statement that ‘‘some of the costs of this 

proposed AD may be covered under 

warranty’’ in the Costs of Compliance 

section of the NPRM (80 FR 25630, May 

5, 2015). Boeing stated that the actions 

in the NPRM are not covered by 

warranty. 

We agree with the commenter’s 

request. We have revised the Costs of 

Compliance section of this final rule 

accordingly. 

Request To Revise Paragraph Headings 

Boeing requested that we revise the 

headings of paragraphs (g), (h), (j), and 

(k) of the proposed AD (80 FR 25630, 

May 5, 2015) by removing reference to 

the inspections as ‘‘repetitive’’ or 

‘‘initial.’’ Boeing stated that these 

revisions will provide consistency 

among paragraph headings because 

paragraphs (g), (j), and (k) of the 

proposed AD do not have an initial 

inspection program, yet paragraph (h) of 

the proposed AD has only an initial 

inspection. 

We acknowledge the commenter’s 

concern and agree to clarify the 

headings. We do not presume that the 

term ‘‘repetitive’’ necessarily excludes 

the initial action. An action cannot be 

repeated without accomplishment of the 

initial action. In addition, in many ADs 

we use the term ‘‘repetitive’’ actions for 

paragraphs that include the initial 

action and repetitive actions. Paragraphs 

(g), (j), and (k) of this AD include both 

a sentence specifying the initial 

inspection and a sentence specifying the 

repetitive inspections. We have not 

changed this AD in this regard. 

Request To Clarify Compliance Time 

Boeing requested that we clarify the 

compliance time in paragraphs (g), (h), 

(j), and (k) of the proposed AD (80 FR 


tkelley on DSK3SPTVN1PROD with RULES