3158 Federal Register / Vol. 80, No. 14 / Thursday, January 22, 2015 / Rules and Regulations 

on an airplane does not constitute 

terminating action for any inspection 

required by paragraph (g) of this AD. 

(2) If, during any inspection required by 

paragraph (g)(1) of this AD, more than one 

discrepancy (any missing or broken or 

migrated fastener) is found on the left- or 

right-side: Before further flight, replace all 

affected fasteners on the affected side(s), in 

accordance with Airbus AOT A57N006–14, 

Revision 00, dated December 4, 2014. One 

fastener per side may be missing or broken 

or migrated provided the applicable actions 

required by paragraph (h)(1) of this AD are 

done. Replacement of fasteners on an 

airplane does not constitute terminating 

action for any inspection required by 

paragraph (g) of this AD. 

(i) Corrective Actions for the Inspections 

Required by Paragraph (g)(2) of This AD 

(1) If, during any inspection required by 

paragraph (g)(2) of this AD, only one 

discrepancy (any missing or broken nut or 

fastener tail) is found on the left- or rightside: Before further flight, do corrective 

actions in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA. Replacement of fasteners 

on an airplane does not constitute 

terminating action for any inspection 

required by paragraph (g) of this AD. 

(2) If, during any inspection required by 

paragraph (g)(2) of this AD, more than one 

discrepancy (any missing or broken nut or 

fastener tail) is found on the left- or rightside: Before further flight, replace all affected 

fasteners on the affected side(s), in 

accordance with Airbus AOT A57N006–14, 

Revision 00, dated December 4, 2014. One 

fastener per side may be missing or broken 

or migrated provided the applicable actions 

required by paragraph (i)(1) of this AD are 

done. Replacement of fasteners on an 

airplane does not constitute terminating 

action for any inspection required by 

paragraph (g) of this AD. 

(j) Special Flight Permits 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(k) Other FAA Provisions 

(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 Manager, International Branch, send it 

to ATTN: Sanjay Ralhan, Aerospace 

Engineer, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 1601 

Lind Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

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 

EASA; or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(l) Related Information 

For further information about this AD, 

contact: Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

(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 the AD specifies otherwise. 

(i) Airbus Alert Operators Transmission 

A57N006–14, Revision 00, dated December 4, 

2014. 

(ii) Reserved. 

(3) For service information referenced in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

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. 

(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 January 

7, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–00716 Filed 1–21–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0580; Directorate 

Identifier 2014–NM–081–AD; Amendment 

39–18062; AD 2015–01–01] 

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) 2011–09– 

11, for certain The Boeing Company 

Model 777–200 and –300 series 

airplanes. AD 2011–09–11 required 

repetitive inspections for hydraulic 

fluid contamination of the interior of the 

strut disconnect assembly; repetitive 

inspections for discrepancies of the 

interior of the strut disconnect 

assembly, if necessary; repetitive 

inspections of the exterior of the strut 

disconnect assembly for cracks, if 

necessary; corrective action if necessary; 

and an optional terminating action for 

the inspections. This new AD adds, for 

certain airplanes, an inspection of the 

side and top cover plates to determine 

if all cover plate attach fasteners have 

been installed, and installing any 

missing fasteners including doing an 

inspection for damage, and repair if 

necessary. This AD was prompted by 

reports of side and top cover plates 

installed with missing fastener bolts, 

which results in an unsealed opening on 

the system disconnect assembly. We are 

issuing this AD to detect and correct 

hydraulic fluid contamination, which 

can cause cracking of titanium parts in 

the system disconnect assembly; and 

also to detect and correct missing 

fasteners, which results in unsealed 

openings on the system disconnect 

assembly. Both unsafe conditions can 

compromise the engine firewall and 

result in fire hazards for both the engine 

compartment and the strut. 

DATES: This AD is effective February 26, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 26, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of June 6, 2011 (76 FR 24354, 

May 2, 2011). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 


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Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.govby searching for 

and locating Docket No. FAA–2014– 

0580; 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: 

Kevin Nguyen, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6501; 

fax: 425–917–6590; email: 

kevin.nguyen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2011–09–11, 

Amendment 39–16673 (76 FR 24354, 

May 2, 2011). AD 2011–09–11 applied 

to The Boeing Company Model 777–200 

and – 300 series airplanes equipped 

with Pratt and Whitney engines. The 

NPRM published in the Federal 

Register on August 26, 2014 (79 FR 

50877). 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

United Airlines and Boeing supported 

the NPRM (79 FR 50877, August 26, 

2014). 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

50877, August 26, 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 50877, 

August 26, 2014). 

Costs of Compliance 

We estimate that this AD affects 54 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspections [retained actions 

from AD 2011-09-11, 

Amendment 39-16673 (76 

FR 24354, May 2, 2011)].

18 work-hours × $85 per hour = $1,530 ................................ $0 $1,530 $82,620 

Inspection of cover plate fasteners [new action].8 work-hours × $85 per hour = $680 ..................................... 0 680 36,720 

We estimate the following costs to do 

any necessary repairs/replacements that 

will be required based on the results of 

the inspections. We have no way of 

determining the number of aircraft that 

might need these repairs/replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement [retained actions from 

AD 2011-09–11, Amendment 39– 

16673 (76 FR 24354, May 2, 

2011)].

35 work-hours × $85 per hour = $2,975 ................................................... $420,440 $423,415 

Inspection of electrical components 

and installation of new fasteners 

[new actions].

14 work-hours × $85 per hour = $1,190 ................................................... 458 1,648 

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 


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is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2011–09–11, Amendment 39–16673 (76 

FR 24354, May 2, 2011), and adding the 

following new AD: 

2015–01–01 The Boeing Company: 

Amendment 39–18062; Docket No. 

FAA–2014–0580; Directorate Identifier 

2014–NM–081–AD. 

(a) Effective Date 

This AD is effective February 26, 2015. 

(b) Affected ADs 

This AD replaces AD 2011–09–11, 

Amendment 39–16673 (76 FR 24354, May 2, 

2011). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200 and –300 series airplanes, 

certificated in any category; equipped with 

Pratt and Whitney engines; as identified in 

Boeing Service Bulletin 777–54A0024, 

Revision 2, dated January 23, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/Pylons. 

(e) Unsafe Condition 

This AD was prompted by reports of side 

and top cover plates installed with missing 

fastener bolts, which results in an unsealed 

opening on the system disconnect assembly. 

We are issuing this AD to detect and correct 

hydraulic fluid contamination, which can 

cause cracking of titanium parts in the 

system disconnect assembly; and also to 

detect and correct missing fasteners, which 

results in unsealed openings on the system 

disconnect assembly. Both unsafe conditions 

can compromise the engine firewall and 

result in fire hazards for both the engine 

compartment and the strut. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspections and Corrective 

Actions With Revised Service Information 

This paragraph restates the requirements of 

paragraph (g) of AD 2011–09–11, 

Amendment 39–16673 (76 FR 24354, May 2, 

2011), with revised service information. 

Within 12 months after June 6, 2011 (the 

effective date of AD 2011–09–11): Do a 

general visual inspection for hydraulic fluid 

contamination of the interior of the strut 

disconnect assembly, in accordance with Part 

1 of the Accomplishment Instructions of 

Boeing Service Bulletin 777–54A0024, 

Revision 1, dated November 4, 2010; or 

Revision 2, dated January 23, 2014. As of the 

effective date of this AD, use only Boeing 

Service Bulletin 777–54A0024, Revision 2, 

dated January 23, 2014, for accomplishing 

the actions in this paragraph. 

(1) For airplanes on which no hydraulic 

fluid contamination is found (Condition 1): 

Repeat the general visual inspection required 

by paragraph (g) of this AD thereafter at 

intervals not to exceed 6,000 flight cycles or 

750 days, whichever occurs first. 

(2) For airplanes on which hydraulic fluid 

contamination is found (Condition 2): Before 

further flight, do a detailed inspection for 

discrepancies (e.g., hydraulic fluid coking, 

heat discoloration, cracks, and etching or 

pitting) of the interior of the strut disconnect 

assembly, in accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–54A0024, Revision 1, 

dated November 4, 2010; or Revision 2, dated 

January 23, 2014. As of the effective date of 

this AD, use only Boeing Service Bulletin 

777–54A0024, Revision 2, dated January 23, 

2014, for accomplishing the actions in this 

paragraph. 

(i) For airplanes on which no discrepancy 

is found during the inspection required by 

paragraph (g)(2) of this AD (Condition 2A): 

Repeat the detailed inspection required by 

paragraph (g)(2) of this AD thereafter at 

intervals not to exceed 6,000 flight cycles or 

750 days, whichever occurs first. 

(ii) For airplanes on which hydraulic fluid 

coking or heat discoloration is found but no 

cracking, etching, or pitting is found during 

the inspection required by paragraph (g)(2) of 

this AD (Condition 2B): Do the actions 

required by paragraph (g)(2)(ii)(A) and 

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

(A) Within 300 flight cycles after doing the 

inspection required by paragraph (g)(2) of 

this AD: Do a detailed inspection of the 

exterior of the strut disconnect assembly for 

cracks, in accordance with Part 3 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–54A0024, Revision 1, 

dated November 4, 2010; or Revision 2, dated 

January 23, 2014; and repeat the detailed 

inspection thereafter at intervals not to 

exceed 300 flight cycles. As of the effective 

date of this AD, use only Boeing Service 

Bulletin 777–54A0024, Revision 2, dated 

January 23, 2014, for accomplishing the 

actions in this paragraph. 

(B) Within 6,000 flight cycles or 750 days 

after hydraulic fluid coking and/or heat 

discoloration was found during the 

inspection required by paragraph (g)(2) of 

this AD, whichever occurs first: Replace the 

titanium system disconnect assembly with an 

Inconel system, in accordance with Part 4 of 

the Accomplishment Instructions of Boeing 

Service Bulletin 777–54A0024, Revision 1, 

dated November 4, 2010; or Revision 2, dated 

January 23, 2014. As of the effective date of 

this AD, use only Boeing Service Bulletin 

777–54A0024, Revision 2, dated January 23, 

2014, for accomplishing the actions in this 

paragraph. 

(h) Retained Corrective Action With Revised 

Service Information 

This paragraph restates the requirements of 

paragraph (h) of AD 2011–09–11, 

Amendment 39–16673 (76 FR 24354, May 2, 

2011), with revised service information. For 

airplanes on which any crack, etching, or 

pitting is found during any inspection 

required by paragraph (g)(2) or (g)(2)(ii)(A) of 

this AD (Condition 3): Before further flight, 

replace the titanium system disconnect 

assembly with an Inconel system, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–54A0024, Revision 1, 

dated November 4, 2010; or Revision 2, dated 

January 23, 2014. As of the effective date of 

this AD, use only Boeing Service Bulletin 

777–54A0024, Revision 2, dated January 23, 

2014, for accomplishing the actions in this 

paragraph. 

(i) Retained Optional Terminating Action 

With Revised Service Information 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–09–11, Amendment 

39–16673 (76 FR 24354, May 2, 2011), with 

revised service information. Replacing the 

titanium system disconnect assembly with an 

Inconel system disconnect assembly in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–54A0024, Revision 1, 

dated November 4, 2010; or Revision 2, dated 

January 23, 2014; terminates the actions 

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

As of the effective date of this AD, use only 

Boeing Service Bulletin 777–54A0024, 


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Revision 2, dated January 23, 2014, for 

accomplishing the actions in this paragraph. 

(j) New Inspection and Corrective Action 

For airplanes on which the system 

disconnect assembly has been replaced in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–54A0024, dated April 1, 

2010; or Revision 1, dated November 4, 2010: 

Within 1,125 days after the effective date of 

this AD, do a detailed inspection of the cover 

plate fasteners to determine if all cover plate 

attach fasteners are installed, in accordance 

with Part 5 of the Accomplishment 

Instructions of Boeing Service Bulletin 777– 

54A0024, Revision 2, dated January 23, 2014. 

If any fastener is missing, before further 

flight, install fasteners (including doing a 

detailed inspection for damage of the 

electrical components and repairing any 

damaged components), in accordance with 

Part 6 of the Accomplishment Instructions of 

Boeing Service Bulletin 777–54A0024, 

Revision 2, dated January 23, 2014. 

(k) Credit for Previous Actions 

This paragraph restates the credit provided 

by paragraph (j) of AD 2011–09–11, 

Amendment 39–16673 (76 FR 24354, May 2, 

2011). This paragraph provides credit for the 

corresponding actions required by 

paragraphs (g), (h), and (i) of this AD, if those 

actions were performed before June 6, 2011 

(the effective date of AD 2011–09–11) using 

Boeing Service Bulletin 777–54A0024, dated 

April 1, 2010, which is not incorporated by 

reference in this AD. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (m)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Kevin Nguyen, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6501; fax: 425–917–6590; 

email: kevin.nguyen@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on February 26, 2015. 

(i) Boeing Service Bulletin 777–54A0024, 

Revision 2, dated January 23, 2014. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on June 6, 2011 (76 FR 

24354, May 2, 2011). 

(i) Boeing Service Bulletin 777–54A0024, 

Revision 1, dated November 4, 2010. 

(ii) Reserved. 

(5) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(6) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

December 22, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–00009 Filed 1–21–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0925; Directorate 

Identifier 2014–NM–229–AD; Amendment 

39–18066; AD 2014–25–52] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A330–200 Freighter, 

–200, and –300 series airplanes and 

Model A340–200, –300, –500, and –600 

series airplanes. This emergency AD 

was sent previously to all known U.S. 

owners and operators of these airplanes. 

This AD requires revising the airplane 

flight manual to advise the flightcrew of 

emergency procedures for abnormal 

Alpha Protection (Alpha Prot). This AD 

was prompted by a report of Angle of 

Attack (AoA) probes jamming on an inservice Airbus Model A321 airplane. We 

are issuing this AD to ensure that the 

flightcrew has procedures to counteract 

the pitch down order due to abnormal 

activation of the Alpha Prot. An 

abnormal Alpha Prot, if not corrected, 

could result in loss of control of the 

airplane. 

DATES: This AD is effective February 6, 

2015 to all persons except those persons 

to whom it was made immediately 

effective by Emergency AD 2014–25–52, 

issued on December 10, 2014, which 

contained the requirements of this 

amendment. 

We must receive comments on this 

AD by March 9, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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– 

0925; or in person at the Docket 

Operations Office 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 (phone: 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 


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