Federal Register / Vol. 79, No. 215 / Thursday, November 6, 2014 / Rules and Regulations 65887 

frequency eddy current inspection (Option 

II), for cracking of the improved tee sections, 

in accordance with the Accomplishment 

Instructions of McDonnell Douglas DC–9 

Alert Service Bulletin A53–231, Revision 2, 

dated June 25, 1993, including Service 

Sketch 3683D, Revision C, dated July 19, 

1989. 

(i) Compliance Times 

(1) For Option I and Option II inspections 

specified in paragraph (h) of this AD: If the 

time of installation of an improved tee 

section having a part number listed in 

paragraph (h) of this AD is known, do the 

initial inspection required by paragraph (h) 

of this AD within 50,000 flight cycles after 

installation of the improved tee section, or 

within 1,500 flight cycles after the effective 

date of this AD, whichever occurs later. 

(2) For Option I and Option II inspections 

specified in paragraph (h) of this AD: If the 

time of installation of an improved tee 

section having a part number identified in 

paragraph (h) of this AD is not known, do the 

initial inspection required by paragraph (h) 

of this AD before the accumulation of 75,000 

total flight cycles, or within 1,500 flight 

cycles after the effective date of this AD, 

whichever occurs later. 

(j) Repetitive Inspections 

If no cracking is found during the 

inspection required by paragraph (h) of this 

AD: Do the actions specified in paragraph 

(j)(1) or (j)(2) of this AD, as applicable, in 

accordance with the Accomplishment 

Instructions of McDonnell Douglas DC–9 

Alert Service Bulletin A53–231, Revision 2, 

dated June 25, 1993, including Service 

Sketch 3683D, Revision C, dated July 19, 

1989. 

(1) For Option I: If Option I was used for 

the inspection required by paragraph (h) of 

this AD, do the actions at the applicable 

intervals, as specified in paragraphs (j)(1)(i), 

(j)(1)(ii), and (j)(1)(iii) of this AD. 

(i) Repeat the LFEC inspection for cracking 

of the side areas above the floor between 

longerons L7 and L17 on the fuselage left and 

right sides, at intervals not to exceed 2,000 

flight cycles. 

(ii) Repeat the general visual inspection for 

cracking of the top and lower areas from 

longeron L7 left side to L7 right side, and 

lower fuselage longeron L17 to L20 on the 

fuselage left and right sides, at intervals not 

to exceed 1,500 flight cycles. 

(iii) Repeat the general visual inspection 

for cracking of the bottom areas from 

longeron L20 left side to L20 right side, at 

intervals not to exceed 3,500 flight cycles. 

(2) For Option II: If Option II was used for 

the inspection required by paragraph (h) of 

this AD, repeat the high and low eddy 

frequency eddy current inspections for 

cracking around the entire periphery of the 

fuselage from the forward side of the 

bulkhead at intervals not to exceed 2,500 

flight cycles. 

(k) Corrective Action and Post-Replacement 

Inspections 

If any cracking is found during any 

inspection required by paragraph (h) or (j) of 

this AD: Before further pressurized flight, 

replace each cracked tee section with an 

airworthy tee section having a part number 

identified in paragraph (h) of this AD, or with 

an original tee section having P/N 5910163– 

89, 5910163–91, 5910163–92, 5910163–93, 

5910163–94, or 5910163–95, in accordance 

with the Accomplishment Instructions of 

McDonnell Douglas DC–9 Alert Service 

Bulletin A53–231, Revision 2, dated June 25, 

1993, including Service Sketch 3683D, 

Revision C, dated July 19, 1989. 

(1) If the tee section is replaced with an 

improved tee section listed in paragraph (h) 

of this AD, prior to the accumulation of 

50,000 flight cycles after installation, inspect 

the tee section in accordance with paragraph 

(h) of this AD and do all applicable corrective 

actions and repetitive inspections in 

accordance with and at the times specified in 

paragraphs (j) and (k) of this AD. 

(2) If the tee section is replaced with an 

original tee section listed in paragraph (k) of 

this AD, prior to the accumulation of 25,000 

flight cycles after installation, inspect the tee 

section in accordance with paragraph (h) of 

this AD and do all applicable corrective 

actions and repetitive inspections in 

accordance with and at the times specified in 

paragraphs (j) and (k) of this AD. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles Certification 

Office (ACO), FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (m) of this AD. Information may be 

emailed to: 9-ANM-LAACO-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, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

(m) Related Information 

For more information about this AD, 

contact Eric Schrieber, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 3960 

Paramount Boulevard, Lakewood, CA 90712– 

4137; phone: 562–627–5348; fax: 562–627– 

5210; email: eric.schrieber@faa.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. 

(i) McDonnell Douglas DC–9 Alert Service 

Bulletin A53–231, Revision 2, dated June 25, 

1993, including Service Sketch 3683D, 

Revision C, dated July 19, 1989. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, CA 90846–0001; 

telephone 206–544–5000, extension 2; fax 

206–766–5683; 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 October 

28, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–26330 Filed 11–5–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0192; Directorate 

Identifier 2013–NM–221–AD; Amendment 

39–17992; AD 2014–20–19] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2013–10– 

06, for all Airbus Model A330–200 

Freighter, A330–200, A330–300, A340– 

200, A340–300, A340–500, and A340– 

600 series airplanes. AD 2013–10–06 

required an inspection to identify the 

installed windshields, and replacement 

of any affected windshield. This new 

AD requires expanding the inspection 

area to 15 additional windshields’ serial 

numbers. This AD was prompted by 

several reports of a burning smell and/ 

or smoke in the cockpit during cruise 

phase, leading in some cases, to 


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diversion to alternate airports. We are 

issuing this AD to prevent significantly 

increased workload for the flightcrew, 

which could, under some flight phases 

and/or circumstances, constitute an 

unsafe condition. 

DATES: This AD becomes effective 

December 11, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 11, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0192; 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. 

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 to supersede AD 2013–10–06, 

Amendment 39–17459 (78 FR 32347, 

May 30, 2013). AD 2013–10–06 applied 

to all Airbus Model A330–200 Freighter, 

A330–200, A330–300, A340–200, A340– 

300, A340–500, and A340–600 series 

airplanes. The NPRM published in the 

Federal Register on April 9, 2014 (79 FR 

19548). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0256, 

dated October 21, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus Model A330–201, –202, 

–203, –223, –223F, –243, –243F, –301, 

–302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model 

A340–211, –212, –213, –311, –312, 

–313, –541, and –642 airplanes. The 

MCAI states: 

Several operators reported cases of burning 

smell and/or smoke in the cockpit during 

cruise phase leading in some cases to 

diversion. Findings showed that the cause of 

these events is the burning of the SaintGobain Sully (SGS) windshield connector 

terminal block. 

This condition, if not corrected, could 

significantly increase the flight crew 

workload which would, under some flight 

phases and/or circumstances constitute an 

unsafe condition. 

To address this unsafe condition, Airbus 

published 3 different Service Bulletins (SB) 

and EASA issued AD 2011–0242 [http://

ad.easa.europa.eu/blob/easa_ad_2011_0242_

Correction_superseded.pdf/AD_2011-0242_1] 

(later corrected) which required the 

identification of the installed windshields 

and replacement of the affected part. 

Since issuance of that [EASA] AD, a new 

occurrence in service led Airbus to identify 

a new batch of affected parts. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2011–0242 [http://ad.easa.europa.eu/

blob/easa_ad_2011_0242_Correction_

superseded.pdf/AD_2011-0242_1], which is 

superseded, and requires identification and 

replacement of the additionally identified 

windshields. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0192- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 19548, April 9, 2014) or on the 

determination of the cost to the public. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

We have become aware that some 

operators have misunderstood or 

misinterpreted the Airworthy Product 

paragraph to allow the owner/operator 

to use messages provided by the 

manufacturer as approval of deviations 

during the accomplishment of an ADmandated action. The Airworthy 

Product paragraph does not approve 

messages or other information provided 

by the manufacturer for deviations to 

the requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed the 

paragraph and retitled it ‘‘Contacting the 

Manufacturer.’’ This paragraph now 

clarifies that for any requirement in this 

AD to obtain corrective actions from a 

manufacturer, the actions must be 

accomplished using a method approved 

by the FAA, the EASA, or Airbus’s 

EASA Design Organization Approval 

(DOA). 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

are EASA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

We also have decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or ‘‘design approval 

holder (DAH) with State of Design 

Authority design organization 

approval,’’ but instead we have 

provided the specific delegation 

approval granted by the State of Design 

Authority for the DAH throughout this 

AD. 


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Conclusion 

We reviewed the relevant data 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 

19548, April 9, 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 19548, 

April 9, 2014). 

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 60 

airplanes of U.S. registry. 

The actions required by AD 2013–10– 

06, Amendment 39–17459 (78 FR 

32347, May 30, 2013), and retained in 

this AD take about 2 work-hours per 

product, at an average labor rate of $85 

per work-hour. Required parts cost 

about $0 per product. Based on these 

figures, the estimated cost of the actions 

that were required by AD 2013–10–06 is 

$170 per product. 

We also estimate that it would take 

about 2 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts would 

cost about $0 per product. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be $10,200, 

or $170 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 10 work-hours and require parts 

costing $0, for a cost of $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/

#!docketDetail;D=FAA-2014-0192; 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 

removing Airworthiness Directive (AD) 

2013–10–06, Amendment 39–17459 (78 

FR 32347, May 30, 2013), and adding 

the following new AD: 

2014–20–19 Airbus: Amendment 39–17992. 

Docket No. FAA–2014–0192; Directorate 

Identifier 2013–NM–221–AD. 

(a) Effective Date 

This AD becomes effective December 11, 

2014. 

(b) Affected ADs 

This AD supersedes AD 2013–10–06, 

Amendment 39–17459 (78 FR 32347, May 30, 

2013). 

(c) Applicability 

This AD applies to all airplanes identified 

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

certificated in any category, all manufacturer 

serial numbers. 

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

–223, –223F, –243, –243F, –301, –302, –303, 

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

airplanes. 

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

–311, –312, –313, –541, and –642 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 56, Windows. 

(e) Reason 

This AD was prompted by several reports 

of a burning smell and/or smoke in the 

cockpit during cruise phase, leading in some 

cases, to diversion to alternate airports. We 

are issuing this AD to prevent significantly 

increased workload for the flightcrew, which 

could, under some flight phases and/or 

circumstances, constitute an unsafe 

condition. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection With Revised Service 

Information 

This paragraph restates the requirements of 

paragraph (g) of AD 2013–10–06, 

Amendment 39–17459 (78 FR 32347, May 30, 

2013), with revised service information. 

Within 1,200 flight hours after July 5, 2013 

(the effective date of AD 2013–10–06), 

inspect to identify the manufacturer, the part 

number, and the serial number of the lefthand (LH) and right-hand (RH) windshields 

installed on the airplane, in accordance with 

the Accomplishment Instructions of the 

applicable Airbus service information 

specified in paragraph (g)(1), (g)(2), or (g)(3) 

of this AD. A review of airplane delivery or 


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maintenance records is acceptable in lieu of 

this inspection if the manufacturer, part 

number, and serial number of the installed 

windshields can be conclusively determined 

from that review. 

(1) For Model A330–201, –202, –203, –223, 

–223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes: 

Airbus Service Bulletin A330–56–3009, 

Revision 02, including Appendix 01, dated 

February 8, 2012; or Airbus Service Bulletin 

A330–56–3009, Revision 03, including 

Appendixes 01 and 02, dated August 1, 2013. 

As of the effective date of this AD, use only 

Airbus Service Bulletin A330–56–3009, 

Revision 03, including Appendixes 01 and 

02, dated August 1, 2013, to do the actions 

required by paragraph (g) of this AD. 

(2) For Model A340–211, –212, –213, –311, 

–312, and –313 airplanes: Airbus Service 

Bulletin A340–56–4008, Revision 01, 

including Appendix 01, dated February 8, 

2012; or Airbus Service Bulletin A340–56– 

4008, Revision 02, including Appendixes 01 

and 02, dated August 1, 2013. As of the 

effective date of this AD, use only Airbus 

Service Bulletin A340–56–4008, Revision 02, 

including Appendixes 01 and 02, dated 

August 1, 2013, to do the actions required by 

paragraph (g) of this AD. 

(3) For Model A340–541 and –642 

airplanes: Airbus Service Bulletin A340–56– 

5002, Revision 01, including Appendix 01, 

dated February 8, 2012; or Airbus Service 

Bulletin A340–56–5002, Revision 02, 

including Appendixes 01 and 02, dated 

August 1, 2013. As of the effective date of 

this AD, use only Airbus Service Bulletin 

A340–56–5002, Revision 02, including 

Appendixes 01 and 02, dated August 1, 2013, 

to do the actions required by paragraph (g) 

of this AD. 

(h) Retained Replacement With Revised 

Service Information 

This paragraph restates the requirements of 

paragraph (h) of AD 2013–10–06, 

Amendment 39–17459 (78 FR 32347, May 30, 

2013), with revised service information. If it 

is found, during the inspection required by 

paragraph (g) of this AD, that any installed 

LH or RH windshield was manufactured by 

Saint-Gobain Sully (SGS) and the part 

number and serial number are specified in 

the applicable Airbus service information 

specified in paragraph (g)(1), (g)(2), or (g)(3) 

of this AD: Within 9 months or 1,200 flight 

hours after July 5, 2013 (the effective date of 

AD 2013–10–06), whichever occurs first, 

replace all affected LH and RH windshields, 

in accordance with the Accomplishment 

Instructions of the applicable Airbus service 

information specified in paragraph (h)(1), 

(h)(2), or (h)(3) of this AD. 

(1) For Model A330–201, –202, –203, –223, 

–223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes: 

Airbus Service Bulletin A330–56–3009, 

Revision 02, including Appendix 01, dated 

February 8, 2012; or Airbus Service Bulletin 

A330–56–3009, Revision 03, including 

Appendixes 01 and 02, dated August 1, 2013. 

As of the effective date of this AD, use only 

Airbus Service Bulletin A330–56–3009, 

Revision 03, including Appendixes 01 and 

02, dated August 1, 2013, to do the actions 

required by paragraph (h) of this AD. 

(2) For Model A340–211, –212, –213, –311, 

–312, and –313 airplanes: Airbus Service 

Bulletin A340–56–4008, Revision 01, 

including Appendix 01, dated February 8, 

2012; or Airbus Service Bulletin A340–56– 

4008, Revision 02, including Appendixes 01 

and 02, dated August 1, 2013. As of the 

effective date of this AD, use only Airbus 

Service Bulletin A340–56–4008, Revision 02, 

including Appendixes 01 and 02, dated 

August 1, 2013, to do the actions required by 

paragraph (h) of this AD. 

(3) For Model A340–541 and –642 

airplanes: Airbus Service Bulletin A340–56– 

5002, Revision 01, including Appendix 01, 

dated February 8, 2012; or Airbus Service 

Bulletin A340–56–5002, Revision 02, 

including Appendixes 01 and 02, dated 

August 1, 2013. As of the effective date of 

this AD, use only Airbus Service Bulletin 

A340–56–5002, Revision 02, including 

Appendixes 01 and 02, dated August 1, 2013, 

to do the actions required by paragraph (h) 

of this AD. 

(i) New Requirement of This AD: Inspection 

Within 6 months after the effective date of 

this AD, inspect to identify the manufacturer, 

the part number, and the serial number of the 

LH and RH windshields installed on the 

airplane, in accordance with the 

Accomplishment Instructions of the 

applicable Airbus service information 

specified in paragraph (i)(1), (i)(2), or (i)(3) of 

this AD. A review of airplane delivery or 

maintenance records is acceptable in lieu of 

this inspection if the manufacturer, part 

number, and serial number of the installed 

windshields can be conclusively determined 

from that review. 

(1) For Model A330–201, –202, –203, –223, 

–223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes: 

Airbus Service Bulletin A330–56–3009, 

Revision 03, including Appendixes 01 and 

02, dated August 1, 2013. 

(2) For Model A340–211, –212, –213, –311, 

–312, and –313 airplanes: Airbus Service 

Bulletin A340–56–4008, Revision 02, 

including Appendixes 01 and 02, dated 

August 1, 2013. 

(3) For Model A340–541 and –642 

airplanes: Airbus Service Bulletin A340–56– 

5002, Revision 02, including Appendixes 01 

and 02, dated August 1, 2013. 

(j) New Requirement of This AD: 

Replacement 

If it is found, during the inspection 

required by paragraph (i) of this AD, that any 

installed LH or RH windshield was 

manufactured by Saint-Gobain Sully (SGS) 

and the part number and serial number are 

specified in Appendix 02 of the applicable 

Airbus service information specified in 

paragraph (j)(1), (j)(2), or (j)(3) of this AD, or 

if the manufacturer or part number or serial 

number is not identifiable: Within 6 months 

after the effective date of this AD, replace the 

affected LH and/or RH windshield with a 

serviceable part, in accordance with the 

Accomplishment Instructions of the 

applicable Airbus service information 

specified in paragraph (j)(1), (j)(2), or (j)(3) of 

this AD. 

(1) For Model A330–201, –202, –203, –223, 

–223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes: 

Airbus Service Bulletin A330–56–3009, 

Revision 03, including Appendixes 01 and 

02, dated August 1, 2013. 

(2) For Model A340–211, –212, –213, –311, 

–312, and –313 airplanes: Airbus Service 

Bulletin A340–56–4008, Revision 02, 

including Appendixes 01 and 02, dated 

August 1, 2013. 

(3) For Model A340–541 and –642 

airplanes: Airbus Service Bulletin A340–56– 

5002, Revision 02, including Appendixes 01 

and 02, dated August 1, 2013. 

(k) Definition of Serviceable Windshield 

For the purposes of this AD, a serviceable 

windshield is a windshield not identified in 

Appendix 01 of the applicable Airbus service 

information as specified in paragraphs (j)(1), 

(j)(2), or (j)(3) of this AD; or it is specified in 

Appendix 01 but has a suffix ‘‘U’’ added to 

the serial number on the identification plate. 

(l) Parts Installation Limitations 

As of the effective date of this AD, no 

person may install, on any airplane, an 

affected windshield from SGS having a part 

number and serial number identified in 

Appendix 01 of the applicable Airbus service 

information as specified in paragraph (l)(1), 

(l)(2), or (l)(3) of this AD, unless a suffix ‘‘U’’ 

has been added on the serial number 

identification plate. 

(1) For Model A330–201, –202, –203, –223, 

–223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes: 

Airbus Service Bulletin A330–56–3009, 

Revision 03, including Appendixes 01 and 

02, dated August 1, 2013. 

(2) For Model A340–211, –212, –213, –311, 

–312, and –313 airplanes: Airbus Service 

Bulletin A340–56–4008, Revision 02, 

including Appendix 01 and 02, dated August 

1, 2013. 

(3) For Model A340–541 and –642 

airplanes: Airbus Service Bulletin A340–56– 

5002, Revision 02, including Appendixes 01 

and 02, dated August 1, 2013. 

(m) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using the applicable 

Airbus service information specified in 

paragraphs (m)(1) through (m)(4) of this AD, 

provided that the actions were accomplished 

on the airplane, and no replacement 

windshield has been installed with a part 

number and serial number identified in 

Appendix 02 of the applicable Airbus service 

information as specified in paragraphs (j)(1) 

through (j)(3) of this AD. 

(1) Airbus Service Bulletin A330–56–3009, 

dated May 4, 2010 (for Model A330–201, 

–202, –203, –223, –223F, –243, –243F, –301, 

–302, –303, –321, –322, –323, –341, –342, 

and –343 airplanes), which is not 

incorporated by reference in this AD. 

(2) Airbus Service Bulletin A330–56–3009, 

Revision 01, dated January 27, 2011 (for 

Model A330–201, –202, –203, –223, –223F, 

–243, –243F, –301, –302, –303, –321, –322, 

–323, –341, –342, and –343 airplanes), which 

is not incorporated by reference in this AD. 

(3) Airbus Service Bulletin A340–56–4008, 

dated May 4, 2010 (for Model A340–211, 


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Federal Register / Vol. 79, No. 215 / Thursday, November 6, 2014 / Rules and Regulations 65891 

–212, –213, –311, –312, and –313 airplanes), 

which is not incorporated by reference in this 

AD. 

(4) Airbus Service Bulletin A340–56–5002, 

dated May 4, 2010 (for Model A340–541 and 

–642 airplanes), which is not incorporated by 

reference in this AD. 

(n) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, FAA, Transport Airplane 

Directorate, 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: As of the 

effective date of this AD, 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. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0256, dated 

October 21, 2013, for related information. 

You may examine the MCAI in the AD 

docket on the Internet at http://www.

regulations.gov/#!documentDetail;D=FAA2014-0192-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(p) 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. 

(i) Airbus Service Bulletin A330–56–3009, 

Revision 03, including Appendixes 01 and 

02, dated August 1, 2013. 

(ii) Airbus Service Bulletin A340–56–4008, 

Revision 02, including Appendix 01 and 02, 

dated August 1, 2013. 

(iii) Airbus Service Bulletin A340–56– 

5002, Revision 02, including Appendixes 01 

and 02, dated August 1, 2013. 

(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 

September 24, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–24964 Filed 11–5–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0232; Directorate 

Identifier 2013–NM–100–AD; Amendment 

39–18010; AD 2014–22–05] 

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 DC–9–10, 

DC–9–20, DC–9–30, DC–9–40, and DC– 

9–50 series airplanes. This AD was 

prompted by an evaluation by the 

design approval holder (DAH) 

indicating that the bulkhead dome tees, 

which connect the bulkhead web to the 

fuselage, are subject to widespread 

fatigue damage (WFD). This AD requires 

repetitive inspections of the improved 

ventral aft pressure bulkhead tees, and 

replacement if necessary. We are issuing 

this AD to detect and correct fatigue 

cracking of the bulkhead dome tees, 

which could result in reduced structural 

integrity and rapid decompression of 

the airplane. 

DATES: This AD is effective December 

11, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 4, 1996 (61 FR 39860, 

July 31, 1996). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, CA 90846–0001; telephone 

206–544–5000, extension 2; fax 206– 

766–5683; 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–2014– 

0232; 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: Eric 

Schrieber, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

CA 90712–4137; phone: 562–627–5348; 

fax: 562–627–5210; email: 

eric.schrieber@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 DC–9–10, DC–9–20, DC–9–30, 

DC–9–40, and DC–9–50 series airplanes. 

The NPRM published in the Federal 

Register on April 17, 2014 (79 FR 

21655). The NPRM was prompted by an 

evaluation by the DAH indicating that 

the bulkhead dome tees, which connect 

the bulkhead web to the fuselage, are 

subject to WFD. The NPRM proposed to 

require repetitive inspections of the 

improved ventral aft pressure bulkhead 

tees, and replacement if necessary. We 

are issuing this AD to detect and correct 


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