73960 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Rules and Regulations 

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 Kansas City, Missouri, on 

November 16, 2015. 

Melvin Johnson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–29855 Filed 11–25–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0928; Directorate 

Identifier 2014–NM–040–AD; Amendment 

39–18333; AD 2015–24–01] 

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 Freighter, 

A330–200, A330–300, A340–200, A340– 

300, A340–500, and A340–600 series 

airplanes. This AD was prompted by a 

report of skin disbonding on a 

composite side panel of a rudder 

installed on an A310 airplane. This AD 

requires a review of the maintenance 

records of the rudder to determine if any 

composite side shell panel repair has 

been done; a thermography inspection 

limited to the repair areas or complete 

side shells, as applicable, to identify 

possible in-service rudder repairs, 

damages, or fluid ingress; and 

applicable related investigative and 

corrective actions. We are issuing this 

AD to detect and correct the rudder skin 

disbonding, which could affect the 

structural integrity of the rudder, and 

could result in reduced controllability 

of the airplane. 

DATES: This AD becomes effective 

January 4, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 4, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0928 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– 

0928. 

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 

Freighter, A330–200, A330–300, A340– 

200, A340–300, A340–500, and A340– 

600 series airplanes. The NPRM 

published in the Federal Register on 

December 29, 2014 (79 FR 77972). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0033, dated February 4, 

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 Freighter, A330–200, 

A330–300, A340–200, A340–300, A340– 

500, and A340–600 series airplanes. The 

MCAI states: 

A case of skin disbonding was reported on 

a composite side panel of a rudder installed 

on an A310 aeroplane. 

The investigation results revealed that this 

disbonding started from a skin panel area 

previously repaired in-service in accordance 

with the Structural Repair Manual (SRM). 

The initial damage has been identified as 

a disbonding between the core and skin of 

the repaired area. This damage may not be 

visually detectable and likely propagates 

during normal operation due to the variation 

of pressure during ground-air-ground cycles. 

Composite rudder side shell panels are also 

installed on A330 and A340 aeroplanes, 

which may have been repaired in-service 

using a similar method. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the rudder, possibly resulting in reduced 

control of the aeroplane. 

For the reasons described above, this 

[EASA] AD requires a one-time 

thermography inspection of a repaired rudder 

or a rudder whose maintenance records are 

incomplete and, depending on findings, 

accomplishment of applicable corrective and 

follow-up actions [including repetitive 

inspections]. 

The related investigative actions in 

this AD include, as applicable, an 

ultrasonic inspection, an elasticity 

laminate checker inspection, a tap test 

inspection, detailed inspections, and 

thermography inspections, and 

ventilation of the core. The repetitive 

inspections include detailed inspections 

and thermography inspections. The 

corrective actions in this AD include 

repairs. 

The compliance time for the related 

investigative actions is before further 

flight after accomplishing the applicable 

inspection required by paragraph (g)(1) 

or (g)(2)(ii) of this AD. 

The intervals for the repetitive 

inspections are either 900 flight hours or 

1,000 flight cycles, depending on the 

applicable conditions identified in the 

service information. 

The compliance times for the 

corrective actions range, depending on 

the applicable conditions identified in 

the service information, from before 

further flight to within 4,500 flight 

cycles but not to exceed 24 months after 

accomplishing the applicable inspection 

required by paragraph (g)(1) or (g)(2)(ii) 

of this AD. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0928- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 77972, 

December 29, 2014) and the FAA’s 

response to each comment. 

Request To Use the Latest Service 

Information 

American Airlines (AAL) and Delta 

Airlines (DAL) requested that we revise 

the NPRM (79 FR 77972, December 29, 

2014) to cite the latest service 

information. 

We agree with the commenters’ 

request. Airbus has issued Airbus 

Service Bulletin A330–55–3043, 

Revision 1, dated August 20, 2014, 

Airbus Service Bulletin A340–55–4039, 

Revision 1, dated August 20, 2014, and 

Airbus Service Bulletin A340–55–5007, 

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Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Rules and Regulations 73961 

Revision 1, dated August 20, 2014. The 

new service information requires no 

additional work, and there are no new 

actions required by this AD. We have 

updated the AD with the latest service 

information, and we have also added a 

credit paragraph for previous actions 

done before the effective date of this AD 

using the service information cited in 

the NPRM (79 FR 77972, December 29, 

2014). 

Request To Clarify the Structural 

Repair Manual Repairs That Are 

Affected 

AAL requested that the NPRM (79 FR 

77972, December 29, 2014) clarify the 

specific structural repair manual (SRM) 

repairs that are affected. AAL stated that 

paragraph (j) of the proposed AD states 

specific serial number ranges that are 

not affected by the AD provided that it 

is determined that no repair has been 

accomplished on the composite side 

shell panel of that rudder since first 

installation on the airplane. AAL 

believes this last sentence is too broad 

and not in line with the intent of the 

service information requirements. AAL 

commented that stating no repair has 

been accomplished limits acceptable 

repairs covered by an Airbus repair 

design approval sheet, designated 

engineering representative repairs, and 

other SRM repairs not affected by the 

improper practices that are the subject 

of the NPRM. AAL stated that 

paragraphs (g)(1) and paragraph (l) of 

the proposed AD list the affected SRM 

repairs in the service information 

figures. 

We agree with the commenter’s 

request. We have revised paragraph (j) 

of this AD to clarify the specific repairs 

accomplished as described in the SRM 

procedures identified in Figure 

A–GBBAA (Sheet 01 and 02) or Figure 

A–GBCAA (Sheet 02) of the service 

information specified in paragraphs 

(g)(1)(i) through (g)(1)(iii) of this AD, as 

applicable. 

Request To Add the Manufacturer Part 

Number 

DAL requested that the NPRM (79 FR 

77972, December 29, 2014) include the 

manufacturer part numbers of the 

rudder serial numbers specified in 

paragraph (j), which provides only a list 

of rudder serial numbers not affected by 

the requirements of paragraphs (g) and 

(h) of the proposed AD. DAL 

commented that in the event of future 

aircraft acquisitions or rudder 

(component only) purchases, operators 

will need the manufacturer part 

numbers associated with the listed 

serial numbers to determine AD 

applicability. 

We disagree with the commenter’s 

request to add part numbers to 

paragraph (j) of this AD. The rudder 

serial number, regardless of the part 

number, is the key to identifying 

whether the rudder is not affected. Only 

rudders that have certain serial numbers 

that meet the conditions specified in 

paragraph (j) of this AD are exempt from 

the actions required by paragraphs (g) 

and (h) of this AD. Airbus has informed 

us that rudders with the same 

manufacturer part number might or 

might not be affected; it is the serial 

number that determines whether it is an 

affected rudder. We have not changed 

the AD 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 (79 FR 

77972, December 29, 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 77972, 

December 29, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information: 

• Airbus Service Bulletin A330–55– 

3043, Revision 1, dated August 20, 

2014. 

• Airbus Service Bulletin A340–55– 

4039, Revision 1, dated August 20, 

2014. 

• Airbus Service Bulletin A340–55– 

5007, Revision 1, dated August 20, 

2014. 

The service information describes 

procedures for a review of the 

maintenance records of the rudder to 

determine if any composite side shell 

panel repair has been done; a 

thermography inspection limited to the 

repair areas or complete side shells, as 

applicable, to identify possible inservice rudder repairs, damages, or fluid 

ingress; and applicable related 

investigative and corrective actions. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section of 

this AD. 

Costs of Compliance 

We estimate that this AD affects 55 

airplanes of U.S. registry. 

We also estimate that it would take 

about 45 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 

$210,375, or $3,825 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

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. 

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73962 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Rules and Regulations 

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-2014-0928; 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): 

2015–24–01 Airbus: Amendment 39–18333. 

Docket No. FAA–2014–0928; Directorate 

Identifier 2014–NM–040–AD. 

(a) Effective Date 

This AD becomes effective January 4, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all airplanes identified 

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

certificated in any category. 

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

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

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

airplanes, all manufacturer serial numbers. 

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

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

all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55, Stabilizers. 

(e) Reason 

This AD was prompted by a report of skin 

disbonding on a composite side panel of a 

rudder installed on an A310 airplane. We are 

issuing this AD to detect and correct the 

rudder skin disbonding, which could affect 

the structural integrity of the rudder, and 

could result in reduced controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Review the Maintenance Records 

Within 24 months after the effective date 

of this AD: Review the maintenance records 

of the rudder to determine if any composite 

side shell panel repair has been 

accomplished on the rudder since first 

installation on an airplane. 

(1) If, based on the maintenance record 

review, any repair identified in Figure A– 

GBBAA (Sheet 01 and 02) or Figure A– 

GBCAA (Sheet 02) of the service information 

specified in paragraphs (g)(1)(i) through 

(g)(1)(iii) of this AD is found: Within 24 

months after the effective date of this AD, do 

a thermography inspection for repair, 

damages, and fluid ingress, limited to the 

repaired areas, in accordance with the 

Accomplishment Instructions of the 

applicable service information specified in 

paragraphs (g)(1)(i) through (g)(1)(iii) of this 

AD: 

(i) Airbus Service Bulletin A330–55–3043, 

Revision 1, dated August 20, 2014 (for Model 

A330–201, –202, –203, –223, –223F, –243, 

–243F, –301, –302, –303, –321, –322, –323, 

–341, –342, and –343 airplanes). 

(ii) Airbus Service Bulletin A340–55–4039, 

Revision 1, dated August 20, 2014 (for Model 

A340–211, –212, –213, –311, –312, and –313 

airplanes). 

(iii) Airbus Service Bulletin A340–55– 

5007, Revision 1, dated August 20, 2014 (for 

Model A340–541 and –642 airplanes). 

(2) For a rudder for which maintenance 

records are unavailable or incomplete, do the 

actions specified in paragraphs (g)(2)(i) and 

(g)(2)(ii) of this AD: 

(i) No later than 3 months before 

accomplishment of the thermography 

inspection, as required by paragraph (g)(2)(ii) 

of this AD, contact Airbus to request related 

rudder manufacturing data by submitting the 

serial number of the rudder to Airbus. 

(ii) Within 24 months after the effective 

date of this AD: Do a thermography 

inspection for any repair on complete side 

shells to identify and mark any repair, in 

accordance with the Accomplishment 

Instructions of the applicable service 

information specified in paragraphs (g)(1)(i) 

through (g)(1)(iii) of this AD. 

(h) Related Investigative Actions, Corrective 

Actions, and Repetitive Inspections 

After the inspection as required by 

paragraph (g)(1) or (g)(2) of this AD: At the 

applicable compliance times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Tables 3, 

4A, 4B, 4C, 4D, and 5 of the applicable 

service information specified in paragraphs 

(g)(1)(i) through (g)(1)(iii) of this AD, 

accomplish all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of the applicable service 

information specified in paragraphs (g)(1)(i) 

through (g)(1)(iii) of this AD; except as 

provided by paragraphs (i)(1) and (i)(2) of 

this AD. Options provided in the service 

information specified in paragraphs (g)(1)(i) 

through (g)(1)(iii) of this AD for 

accomplishing the actions are acceptable for 

the corresponding requirements of this 

paragraph provided that the related 

investigative and corrective actions are done 

at the applicable times specified in paragraph 

1.E., ‘‘Compliance,’’ of the applicable service 

information specified in paragraphs (g)(1)(i) 

through (g)(1)(iii) of this AD, including 

applicable repetitive inspection intervals, 

except as required by paragraphs (i)(1) and 

(i)(2) of this AD. Thereafter repeat the 

inspections of the restored and repaired areas 

at the applicable compliance time specified 

in paragraph 1.E., ‘‘Compliance,’’ of Tables 3, 

4A, 4B, 4C, 4D, and 5 of the applicable 

service information specified in paragraphs 

(g)(1)(i) through (g)(1)(iii) of this AD. 

(i) Exceptions to the Service Information 

(1) Where the applicable service 

information specified in paragraphs (g)(1)(i) 

through (g)(1)(iii) of this AD specifies a 

compliance time relative to the date of the 

service information, this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(2) If the service information in paragraphs 

(g)(1)(i) through (g)(1)(iii) of this AD specifies 

to contact Airbus: At the applicable 

compliance times specified in paragraph 1.E., 

‘‘Compliance,’’ of the applicable service 

information specified in paragraphs (g)(1)(i) 

through (g)(1)(iii) of this AD, repair 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). 

(j) Provisions for Certain Airplanes 

Airplanes fitted with a rudder having a 

serial number (S/N) that is not in the range 

of S/N TS–1001 through S/N TS–1043 

inclusive, S/N TS–2001 through S/N TS– 

2074 inclusive, S/N TS–3000 through S/N 

TS–3525 inclusive, S/N TS–4001 through 

S/N TS–4170 inclusive, S/N TS–6001 

through S/N TS–6246 inclusive, or S/N TS– 

5001 through S/N TS–5138 inclusive, are not 

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Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Rules and Regulations 73963 

affected by the requirements of paragraphs (g) 

and (h) of this AD provided that it is 

determined that no repair has been 

accomplished as described in the procedures 

identified in Figure A–GBBAA (Sheet 01 and 

02) or Figure A–GBCAA (Sheet 02) of the 

service information specified in paragraphs 

(g)(1)(i) through (g)(1)(iii) of this AD, as 

applicable, on the composite side shell panel 

of that rudder since first installation on an 

airplane. 

(k) Parts Installation Limitations 

As of the effective date of this AD, no 

person may install, on any airplane, a rudder, 

unless the record review and thermography 

inspection specified in paragraph (g) of this 

AD has been done on that rudder and 

thereafter all applicable related investigative 

actions, repetitive inspections, and corrective 

actions are done as required by paragraph (h) 

of this AD, except as provided in paragraph 

(j) of this AD. 

(l) Repair Prohibition 

As of the effective date of this AD, no 

person may accomplish a side shell repair on 

any rudder using a structure repair manual 

procedure identified in Figure A–GBBAA 

(Sheet 01 and 02) or Figure A–GBCAA (Sheet 

02) of the service information specified in 

paragraphs (g)(1)(i) through (g)(1)(iii) of this 

AD, as applicable, on any airplane. 

(m) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in this AD, if those actions 

were performed before the effective date of 

this AD using the service information in 

paragraphs (m)(1), (m)(2), and (m)(3) of this 

AD. 

(1) Airbus Service Bulletin A330–55–3043, 

dated February 7, 2013. 

(2) Airbus Service Bulletin A340–55–4039, 

dated February 7, 2013. 

(3) Airbus Service Bulletin A340–55–5007, 

dated February 7, 2013. 

(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, 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 EASA; or Airbus’s EASA 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 2014–0033, dated 

February 4, 2014, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2014–0928. 

(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 A330–55–3043, 

Revision 1, dated August 20, 2014. 

(ii) Airbus Service Bulletin A340–55–4039, 

Revision 1, dated August 20, 2014. 

(iii) Airbus Service Bulletin A340–55– 

5007, Revision 1, dated August 20, 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 

November 9, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–29851 Filed 11–25–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–1048; Directorate 

Identifier 2014–NM–055–AD; Amendment 

39–18332; AD 2015–23–14] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Fokker Services B.V. Model F.28 Mark 

0070 and 0100 airplanes. This AD was 

prompted by reports that cracks can 

occur in a frame of the tail section on 

certain airplanes. This AD requires a 

one-time detailed inspection of the 

oblique frame 67–2 for any cracking, 

and repair if necessary. We are issuing 

this AD to detect and correct such 

cracking, which could lead to failure of 

the oblique frame 67–2, and consequent 

loss of the structural integrity of the tail 

section. 

DATES: This AD becomes effective 

January 4, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 4, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-1048 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 Fokker Services B.V., 

Technical Services Dept., P.O. Box 

1357, 2130 EL Hoofddorp, the 

Netherlands; telephone +31 (0)88–6280– 

350; fax +31 (0)88–6280–111; email 

technicalservices@fokker.com; Internet 

http://www.myfokkerfleet.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– 

1048. 

mstockstill on DSK4VPTVN1PROD with RULES