Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations 80239 

conditions specified in both paragraphs (h)(1) 

and (h)(2) of this AD are met. 

(1) The action was performed before the 

effective date of this AD using Bombardier 

Service Bulletin 605–24–007, Bombardier 

Service Bulletin 604–24–026, or Bombardier 

Service Bulletin 601–0625, all dated 

September 18, 2012. This service information 

is not incorporated by reference in this AD. 

(2) The action specified in Service Request 

for Product Support Action (SRPSA) 27512, 

SRPSA 30806, SRPSA 32727, SRPSA 32864, 

or SRPSA 33161 has not been done. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 New York ACO, send it to 

ATTN: Program Manager, Continuing 

Operational Safety, FAA, New York ACO, 

1600 Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7300; fax 

516–794–553. 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, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

Transport Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–05, dated 

January 20, 2014, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/#!documentDetail;D=

FAA-2014-0625-0003. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Bombardier Service Bulletin 605–24– 

007, Revision 01, dated January 13, 2014. 

(ii) Bombardier Service Bulletin 604–24– 

026, Revision 01, dated January 13, 2014. 

(iii) Bombardier Service Bulletin 601–0625, 

Revision 01, dated January 13, 2014. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 Coˆte 

Vertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.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 

December 8, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–31604 Filed 12–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0083; Directorate 

Identifier 2014–NM–131–AD; Amendment 

39–18347; AD 2015–25–09] 

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 certain 

Airbus Model A330–200, A330–200 

Freighter, and A330–300 series 

airplanes; and all Model A340–200 and 

A340–300 series airplanes. This AD was 

prompted by reports that a bracket that 

attaches the cockpit instrument panel to 

the airplane structure does not sustain 

the fatigue loads of the design service 

goal. This AD requires repetitive 

inspections of that bracket for cracking 

and to determine if both lugs are fully 

broken, an inspection for cracking of an 

adjacent bracket if necessary, and 

corrective actions if necessary. This AD 

also provides an optional modification, 

which terminates the repetitive 

inspections. We are issuing this AD to 

detect and correct cracking on a bracket 

of the cockpit instrument panel, which, 

combined with failure of the horizontal 

beam, could lead to collapse of the 

cockpit panel, and reduced 

controllability of the airplane. 

DATES: This AD becomes effective 

January 28, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 28, 2016. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-0083; 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 final rule, 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–2015– 

0083. 

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 certain Airbus Model A330– 

200, A330–200 Freighter, and A330–300 

series airplanes; and all Model A340– 

200 and A340–300 series airplanes. The 

NPRM published in the Federal 

Register on February 13, 2015 (80 FR 

7989). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0127, dated May 15, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Airbus 

Model A330–200, A330–200 Freighter, 


tkelley on DSK3SPTVN1PROD with RULES
80240 Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations 

and A330–300 series airplanes; and all 

Model A340–200, and A340–300 series 

airplanes. The MCAI states: 

During flight tests, high stress levels have 

been measured on the bracket No 6 which 

attaches the cockpit instrument panel to the 

aeroplane structure, apparently introduced 

through the nose landing gear due to bumps 

on the runway. Airbus determined that the 

bracket does not sustain the fatigue loads 

during the Design Service Goal (DSG). 

This condition, if not detected and 

corrected, combined with failure of the 

horizontal beam, could lead to collapse of the 

cockpit panel, possibly resulting in reduced 

control of the aeroplane. 

To address this potential unsafe condition, 

Airbus developed a program to inspect the 

condition of the affected cockpit instrument 

panel bracket No 6, and designed a stronger 

(reinforced titanium undrilled) bracket. The 

new bracket can be installed in-service 

through Airbus Service Bulletin (SB) A330– 

25–3548 or SB A340–25–4354, as applicable 

to aeroplane type. 

For the reasons described above, this 

[EASA] AD requires repetitive inspections of 

the cockpit instrument panel bracket No 6 

and, depending on findings, the 

accomplishment of applicable corrective 

actions. This [EASA] AD also provides the 

installation of the stronger bracket as 

optional terminating action for the repetitive 

actions required by this [EASA] AD. 

The corrective actions include replacing 

bracket No. 6 and bracket No. 7 with 

serviceable parts, and repair, as 

applicable. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-0083- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

The following presents the comment 

received on the NPRM (80 FR 7989, 

February 13, 2015) and the FAA’s 

response. 

Request To Identify Part Numbers in 

Paragraphs (g) and (h) 

Delta Airlines requested that 

paragraphs (g) and (h) of the proposed 

AD (80 FR 7989, February 13, 2015) be 

revised to specify the part numbers of 

the affected brackets. Delta suggested 

that paragraph (g) of the proposed AD be 

revised to include the part number after 

the reference to bracket No. 6 (part 

number (P/N) F2511012820000, premodification Number 55128S18242; and 

P/N F2511373420000, post-modification 

Number 55128S18242). Delta also 

requested that paragraph (h)(2) of the 

proposed AD be revised to include the 

part number after bracket No. 6 (P/N 

F2511012820000, pre-modification 

Number 55128S18242; and P/N 

F2511373420000, post-modification 

Number 55128S18242) and bracket No. 

7 (P/N F2511012820000, premodification Number 55128S18242; and 

P/N F2511373420000, post-modification 

Number 55128S18242). Delta stated that 

Airbus Service Bulletin A330–25–3538, 

Revision 02, dated April 24, 2014, 

specifies to inspect only P/N 

F2511012820000, pre-modification 

Number 55128S18242, and P/N 

F2511373420000, post-modification 

Number 55128S18242, and identifies 

only those part numbers as ‘‘affected’’ 

brackets that are used on both bracket 

No. 6 and bracket No. 7. 

We agree to include the part numbers 

identified by the commenter in 

paragraphs (g) and (h)(2) of this AD. We 

have also included the part numbers in 

paragraphs (h)(1) and (h)(2)(i) of this 

AD. The ‘‘Reason/Description/

Operational Consequences’’ section of 

Airbus Service Bulletin A330–25–3538, 

Revision 02, dated April 24, 2014, 

specifies to inspect P/N 

F2511012820000, pre-modification 

Number 55128S18242, and P/N 

F2511373420000, post-modification 

Number 55128S18242. Also, the 

Accomplishment Instructions of that 

service bulletin specify to replace P/N 

F2511012820000 or P/N 

F2511373420000, as applicable. We 

contacted Airbus for verification that 

only those part numbers are considered 

to be ‘‘affected’’ brackets and Airbus 

confirmed that only those part numbers 

are affected. The same affected and 

replacement parts are used on both 

Airbus Model A330–200, A330–200 

Freighter, and A330–300 series 

airplanes; and A340–200 and A340–300 

series airplanes. 

Additional Change to This AD 

A typographical error in paragraph 

(c)(1) of the proposed AD (80 FR 7989, 

February 13, 2015) has been corrected in 

this final rule. Paragraph (c)(1) of the 

proposed AD inadvertently included 

Model A330–313 airplanes instead of 

Model A330–343 airplanes. The 

SUMMARY section and preamble of the 

NPRM stated that the applicability 

included Model A330–300 series 

airplanes, which include Model A330– 

343 airplanes. 

Conclusion 

We reviewed the relevant data, 

considered the comment 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 7989, 

February 13, 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 7989, 

February 13, 2015). 

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 A330–25– 

3538, Revision 02, dated April 24, 2014, 

which provides procedures for 

inspection of cockpit instrument panel 

bracket 6. 

• Airbus Service Bulletin A330–25– 

3548, dated October 31, 2013, which 

provides procedures for replacement of 

cockpit instrument panel bracket 6 with 

a reinforced titanium bracket. 

• Airbus Service Bulletin A340–25– 

4351, Revision 01, dated January 31, 

2014, which provides procedures for 

inspection of cockpit instrument panel 

bracket 6. 

• Airbus Service Bulletin A340–25– 

4354, dated October 31, 2013, which 

provides procedures for replacement of 

cockpit instrument panel bracket 6 with 

a reinforced titanium bracket. 

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. 

Costs of Compliance 

We estimate that this AD affects 76 

airplanes of U.S. registry. 

We also estimate that it will take 

about 8 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 $51,680, or $680 per 

product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the follow-on repairs 

specified in this AD. 

In addition, we estimate that any 

necessary replacements will take about 

23 work-hours and require parts costing 

$0, for a cost of $1,955 per product. We 

have no way of determining the number 

of aircraft that might need these actions. 

We estimate that the optional 

modification will take about 9 work 

hours and require parts costing $1,770, 

for a cost of $2,535. 


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Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations 80241 

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-2015-0083; 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): 

2015–25–09 Airbus: Amendment 39–18347. 

Docket No. FAA–2015–0083; Directorate 

Identifier 2014–NM–131–AD. 

(a) Effective Date 

This AD becomes effective January 28, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

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

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

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

all manufacturer serial numbers except those 

on which Airbus Modification 203287 has 

been embodied in production. 

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

–312, and –313 airplanes, all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/Furnishings. 

(e) Reason 

This AD was prompted by reports that a 

bracket that attaches the cockpit instrument 

panel to the airplane structure does not 

sustain the fatigue loads of the design service 

goal. We are issuing this AD to detect and 

correct cracking on a bracket of the cockpit 

instrument panel, which, combined with 

failure of the horizontal beam, could lead to 

collapse of the cockpit panel, and reduced 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection of Bracket No. 6 of the Cockpit 

Instrument Panel 

At the latest of the times specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD: 

Do a detailed inspection of bracket No. 6 

(part number (P/N) F2511012820000, premodification Number 55128S18242; or P/N 

F2511373420000, post-modification Number 

55128S18242) of the cockpit instrument 

panel for cracking and to determine if both 

bracket lugs are fully broken, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A330–25–3538, 

Revision 02, dated April 24, 2014; or Airbus 

Service Bulletin A340–25–4351, Revision 01, 

dated January 31, 2014; as applicable. Repeat 

the inspection thereafter at intervals not to 

exceed 2,600 flight cycles. 

(1) Prior to accumulating 17,200 total flight 

cycles since the airplane’s first flight. 

(2) Prior to bracket No. 6 of the cockpit 

instrument panel accumulating 17,200 total 

flight cycles since installation on an airplane. 

(3) Within 500 flight cycles after the 

effective date of this AD. 

(h) Inspection and Corrective Actions 

(1) If, during any inspection required by 

paragraph (g) of this AD, any cracking of 

bracket No. 6 (P/N F2511012820000, premodification Number 55128S18242; or P/N 

F2511373420000, Post-modification Number 

55128S18242) of the cockpit instrument 

panel is found, and both bracket lugs are not 

fully broken: Within 2,600 flight cycles after 

that inspection, replace bracket No. 6 of the 

cockpit instrument panel with a serviceable 

part, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–25–3538, Revision 02, 

dated April 24, 2014; or Airbus Service 

Bulletin A340–25–4351, Revision 01, dated 

January 31, 2014; as applicable. Replacement 

of bracket No. 6 (P/N F2511012820000, premodification Number 55128S18242; or P/N 

F2511373420000, post-modification Number 

55128S18242) of the cockpit instrument 

panel does not constitute terminating action 

for the repetitive inspections required by 

paragraph (g) of this AD. 

(2) If, during any inspection required by 

paragraph (g) of this AD, any cracking of 

bracket No. 6 (P/N F2511012820000, premodification Number 55128S18242; or P/N 

F2511373420000, Post-modification Number 

55128S18242) of the cockpit instrument 

panel is found and both bracket lugs are fully 

broken: Before further flight, do a detailed 

inspection of bracket No. 7 (P/N 

F2511012820000, pre-modification Number 

55128S18242; or P/N F2511373420000, Postmodification Number 55128S18242) of the 

cockpit instrument panel for cracking, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

25–3538, Revision 02, dated April 24, 2014; 

or Airbus Service Bulletin A340–25–4351, 

Revision 01, dated January 31, 2014; as 

applicable. 

(i) If, during the inspection required by 

paragraph (h)(2) of this AD, no cracking is 

found in bracket No. 7 of the cockpit 

instrument panel: Before further flight, 

replace bracket No. 6 and bracket No. 7 of the 

cockpit instrument panel with serviceable 

parts, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–25–3538, Revision 02, 

dated April 24, 2014; or Airbus Service 

Bulletin A340–25–4351, Revision 01, dated 

January 31, 2014; as applicable. Replacement 

of bracket No. 6 (P/N F2511012820000, preVerDate Sep<11>2014 17:12 Dec 23, 2015 Jkt 238001 PO 00000 Frm 00035 Fmt 4700 Sfmt 4700 E:\FR\FM\24DER1.SGM 24DER1

tkelley on DSK3SPTVN1PROD with RULES
80242 Federal Register / Vol. 80, No. 247 / Thursday, December 24, 2015 / Rules and Regulations 

modification Number 55128S18242; or P/N 

F2511373420000, post-modification Number 

55128S18242) of the cockpit instrument 

panel does not constitute terminating action 

for the repetitive inspections required by 

paragraph (g) of this AD. 

(ii) If, during the inspection required by 

paragraph (h)(2) of this AD, any cracking is 

found in bracket No. 7 of the cockpit 

instrument panel: Although Airbus Service 

Bulletin A330–25–3538, Revision 02, dated 

April 24, 2014; and Airbus Service Bulletin 

A340–25–4351, Revision 01, dated January 

31, 2014; specify to contact Airbus for repair 

instructions, and specify that action as ‘‘RC’’ 

(Required for Compliance), repair the 

cracking before further flight using a repair 

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). 

(i) Optional Terminating Modification for 

Paragraph (g) of This AD 

Modifying an airplane by replacing bracket 

No. 6 of the cockpit instrument panel with 

a new, reinforced bracket, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A330–25–3548, dated 

October 31, 2013; or Airbus Service Bulletin 

A340–25–4354, dated October 31, 2013; as 

applicable; terminates the repetitive 

inspections required by paragraph (g) of this 

AD. 

(j) 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 service 

information identified in paragraph (j)(1), 

(j)(2), or (j)(3) of this AD, which is not 

incorporated by reference in this AD. 

(1) Airbus Service Bulletin A330–25–3538, 

dated September 10, 2013. 

(2) Airbus Service Bulletin A330–25–3538, 

Revision 01, dated April 24, 2014. 

(3) Airbus Service Bulletin A340–25–4351, 

dated September 10, 2014. 

(k) 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. 

(3) Required for Compliance (RC): Except 

as required by paragraph (h)(2)(ii) of this AD, 

if Airbus Service Bulletin A330–25–3538, 

Revision 02, dated April 24, 2014; or Airbus 

Service Bulletin A340–25–4351, Revision 01, 

dated January 31, 2014; contain procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures and tests that 

are not identified as RC are recommended. 

Those procedures and tests that are not 

identified as RC may be deviated from, using 

accepted methods in accordance with the 

operators maintenance or inspection program 

without obtaining approval of an AMOC, 

provided the procedures and tests identified 

as RC can be done and the airplane can be 

put back in an airworthy condition. Any 

substitutions or changes to procedures or 

tests identified as RC require approval of an 

AMOC. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0127, dated 

May 15, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

#!documentDetail;D=FAA-2015-0083-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(m) 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 A330–25–3538, 

Revision 02, dated April 24, 2014. 

(ii) Airbus Service Bulletin A330–25–3548, 

dated October 31, 2013. 

(iii) Airbus Service Bulletin A340–25– 

4351, Revision 01, dated January 31, 2014. 

(iv) Airbus Service Bulletin A340–25– 

4354, dated October 31, 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 

December 9, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–31714 Filed 12–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0828; Directorate 

Identifier 2014–NM–146–AD; Amendment 

39–18341; AD 2015–25–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2013–23– 

03, which applies to certain The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747–400, 747– 

400D, 747–400F, and 747SR series 

airplanes. AD 2013–23–03 required a 

detailed inspection of certain attach 

fittings for a cylindrical defect, and 

replacement if necessary. For certain 

airplanes, this new AD requires new 

inspections of the inboard actuator 

attach fittings for machining defects, 

and overhaul or replacement if 

necessary. This new AD also limits the 

compliance time for doing the 

replacement for certain other airplanes. 

This AD was prompted by a report that 

a machining defect was also found on 

some of the actuator assemblies 

inspected during manufacture. This 

defect could lead to fatigue cracking and 

subsequent fracture. We are issuing this 

AD to detect and correct defective 

inboard actuator attach fittings which, 

combined with loss of the outboard 

actuator load path, could result in 

uncontrolled retraction of the outboard 

flap, damage to flight control systems, 

and consequent reduced controllability 

of the airplane. 

DATES: This AD is effective January 28, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 


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