Federal Register / Vol. 80, No. 14 / Thursday, January 22, 2015 / Rules and Regulations 3155 

FIGURE 1 TO PARAGRAPH (g) OF THIS AD—AFM PROCEDURE

• At any time, with a speed above VLS, if the aircraft goes to a continuous nose down pitch rate that cannot be stopped with backward sidestick inputs, immediately: 

Keep on one ADR. 

Turn off two ADRs. 

• If the Alpha Max strip (red) hides completely the Alpha Prot strip (black and amber) in a stabilized wings-level flight path (without 

an increase in load factor): 

Keep on one ADR. 

Turn off two ADRs. 

In case of dispatch with one ADR inoperative, switch only one ADR to OFF. 

• CAUTION RISK OF ERRONEOUS DISPLAY OF THE VSW STRIP (RED AND BLACK) 

Consider using the Flight Path Vector (FPV). 

• If the Alpha Prot strip (black and amber) rapidly moves by more than 30 kt during flight maneuvers (with an increase in load factor), with AP ON and speed brakes retracted: 

Keep on one ADR. 

Turn off two ADRs. 

In case of dispatch with one ADR inoperative, switch only one ADR to OFF. 

CAUTION RISK OF ERRONEOUS DISPLAY OF THE VSW STRIP (RED AND BLACK) 

Consider using the Flight Path Vector (FPV). 

(h) 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. 

(i) 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 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. 

(j) Related Information 

For more 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. 

(k) Material Incorporated by Reference 

None. 

Issued in Renton, Washington, on January 

7, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–00714 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–2014–0927; Directorate 

Identifier 2014–NM–230–AD; Amendment 

39–18068; AD 2014–26–53] 

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 certain 

Airbus Model A319–115, A319–133, 

A320–214, A320–232, and A320–233 

airplanes. This emergency AD was sent 

previously to all known U.S. owners 

and operators of these airplanes. This 

AD requires repetitive detailed visual 

inspections to detect discrepancies of 

the wing lower skin surface and inboard 

main landing gear (MLG) support rib 

lower flange location fasteners and, 

depending on findings, accomplishment 

of applicable corrective action(s). This 

AD was prompted by reports of failure 

of certain fasteners located at the wing 

lower skin surface and inboard MLG 

support rib lower flange. We are issuing 

this AD to detect and correct 

discrepancies of the fasteners at the 

external surface of the lower wing skin 

and inboard MLG support rib lower 

flange, which could result in an airplane 

not meeting its maximum loads 

expected in service. This condition 

could result in structural failure. 

DATES: This AD is effective February 6, 

2015 to all persons except those persons 

to whom it was made immediately 

effective by Emergency AD 2014–26–53, 

issued on December 16, 2014, which 

contained the requirements of this 

amendment. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication identified in this 

AD as of February 6, 2015. 

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. 

For service information identified 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.airwortheas@airbus.com; Internet http://

www.airbus.com. 


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3156 Federal Register / Vol. 80, No. 14 / Thursday, January 22, 2015 / Rules and Regulations 

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– 

0927; 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: 

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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On December 16, 2014, we issued 

Emergency AD 2014–26–53, which 

requires repetitive detailed visual 

inspections to detect discrepancies of 

the wing lower skin surface and inboard 

MLG support rib lower flange location 

fasteners and, depending on findings, 

accomplishment of applicable corrective 

action(s). Corrective actions include 

fastener replacement or repair. This 

emergency AD was sent previously to 

all known U.S. owners and operators of 

these airplanes. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued Airworthiness 

Directive 2014–0270R1, dated December 

15, 2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on certain Airbus 

Model A319–115, A319–133, A320–214, 

A320–232, and A320–233 airplanes. 

The MCAI states: 

During production of wings, a number of 

taperlok fasteners were found failed after 

installation. The fasteners in question are 

located at the bottom skin of the Main 

Landing Gear (MLG) reinforcing plate, wing 

skin and Gear Support Rib 5 lower flange. 

This condition, if not detected and 

corrected could reduce the design margin of 

the structure [and could result in structural 

failure]. 

Based on the results of the preliminary 

investigation, this affects only certain A319 

and A320 aeroplane Models delivered since 

January 2014. A321 aeroplanes are not 

affected, as the wing assembly is done using 

parallel fasteners. A318 aeroplanes are not 

affected, since none have been delivered 

since January 2014. 

Prompted by these findings, EASA issued 

Emergency AD 2014–0270–E [dated 

December 11, 2014] to require repetitive 

inspections of the bottom skin taperlok 

fasteners at the MLG Rib 5 footprint location 

and, depending on findings, accomplishment 

of applicable corrective action(s). 

Since that AD was issued, operator 

comments have indicated the need for 

clarification, as well as correction. 

For the reason described above, this 

[EASA] AD is revised to add Notes for 

information and to correct paragraphs (1) and 

(2) of the AD. 

This [EASA] AD is still considered to be 

an interim action and further AD action may 

follow. 

Related Service Information 

Airbus has issued Airbus Alert 

Operators Transmission (AOT) 

A57N006–14, Revision 00, dated 

December 4, 2014. The service 

information describes procedures for 

inspections of the bottom skin fasteners 

at the MLG rib 5 footprint location, and 

replacement of affected fasteners. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. You can find this information at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2014– 

0927. 

FAA’s Determination and AD 

Requirements 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

EASA Airworthiness Directive 2014– 

0270–E, dated December 11, 2014, 

specifies to do repetitive detailed visual 

inspections of the outboard MLG 

support rib lower flange fasteners and 

nuts. However, these inspections are not 

required by this AD. Since the specified 

compliance time is four months, we are 

considering further rulemaking to 

require those inspections. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because discrepancies of the 

fasteners at the external surface of the 

lower wing skin and inboard MLG 

support rib lower flange could result in 

an airplane not meeting its maximum 

loads expected in-service. This 

condition could result in structural 

failure. Therefore, we find that notice 

and opportunity for prior public 

comment are impracticable and that 

good cause exists for making this 

amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2014–0927 and Directorate 

Identifier 2014–NM–230–AD at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects 80 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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Federal Register / Vol. 80, No. 14 / Thursday, January 22, 2015 / Rules and Regulations 3157 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection ...................... 1 work-hour × $85 per hour = $85 [per inspection cycle].$0 $85 [per inspection 

cycle].

$6,800 [per inspection 

cycle]. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Replacement ........................ 3 work-hours × $85 per hour = $255 [per fastener replacement].$400 [per fastener] ............ $655 [per fastener replacement]. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition repairs 

specified in this AD. 

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 

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 adding 

the following new airworthiness 

directive (AD): 

2014–26–53 Airbus: Amendment 39–18068; 

Docket No. FAA–2014–0927; Directorate 

Identifier 2014–NM–230–AD. 

(a) Effective Date 

This AD is effective February 6, 2015 to all 

persons except those persons to whom it was 

made immediately effective by Emergency 

AD 2014–26–53, issued on December 16, 

2014, which contained the requirements of 

this amendment. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A319– 

115, A319–133, A320–214, A320–232, and 

A320–233 airplanes, certificated in any 

category, manufacturer serial numbers (MSN) 

5817, 5826, 5837, 5848, 5855, 5864, 5875, 

5886, 5896, and 5910, and MSNs 5918 and 

subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of failure 

of certain fasteners located at the wing lower 

skin surface and inboard main landing gear 

(MLG) support rib lower flange. We are 

issuing this AD to detect and correct 

discrepancies of the fasteners at the external 

surface of the lower wing skin and inboard 

MLG support rib lower flange, which could 

result in an airplane not meeting its 

maximum loads expected in-service. This 

condition could result in structural failure. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Within 8 days after the effective date of 

this AD, or within 8 days since the date of 

issuance of the original certificate of 

airworthiness or the original export 

certificate of airworthiness, or before further 

flight for any airplane that is not in 

operation, whichever occurs later: Do the 

inspections required by paragraphs (g)(1) and 

(g)(2) of this AD, in accordance with Airbus 

Alert Operators Transmission (AOT) 

A57N006–14, Revision 00, dated December 4, 

2014. Repeat the inspections thereafter at 

intervals not to exceed 8 days. 

(1) Do a detailed visual inspection of the 

external surface of the left-hand and righthand wing lower skin surface to detect 

missing or broken or migrated fasteners. 

(2) Do a detailed visual inspection of the 

inboard MLG support rib lower flange to 

detect missing or broken nuts or fastener 

tails. 

(h) Corrective Actions for the Inspections 

Required by Paragraph (g)(1) of This AD 

(1) If, during any inspection required by 

paragraph (g)(1) of this AD, only one 

discrepancy (any missing or broken or 

migrated fastener) is found on the left- or 

right-side: 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 


tkelley on DSK3SPTVN1PROD with RULES
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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