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cabin floor beam junction at certain fuselage 

frame locations. We are issuing this AD to 

detect and correct cracking in the cabin floor 

beam junction at certain fuselage frame 

locations, which could result in reduced 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Before exceeding 36,900 total flight cycles 

since first flight of the airplane, or within 

2,100 flight cycles after the effective date of 

this AD, whichever occurs later: Do a 

detailed inspection for cracking of the frame 

to cabin floor beam junction on the aft and 

forward sides at frame (FR) 35.1 and FR 35.2 

on the left-hand and right-hand sides, in 

accordance with the Accomplishment 

Instructions of the Airbus service information 

specified in paragraphs (g)(1), (g)(2), (g)(3), 

and (g)(4) of this AD. Repeat the inspection 

of the frame to cabin floor beam junction on 

the aft and forward sides at FR 35.1 and FR 

35.2 on the left-hand and right-hand sides 

thereafter at intervals not to exceed 15,300 

flight cycles. 

(1) Airbus Service Bulletin A320–53–1317, 

dated December 15, 2015 (FR 35.1 right-hand 

side). 

(2) Airbus Service Bulletin A320–53–1318, 

dated October 9, 2015 (FR 35.1 left-hand 

side). 

(3) Airbus Service Bulletin A320–53–1319, 

dated October 9, 2015 (FR 35.2 right-hand 

side). 

(4) Airbus Service Bulletin A320–53–1320, 

dated October 9, 2015 (FR 35.2 left-hand 

side). 

(h) Repair 

If any crack is found during any inspection 

required by paragraph (g) of this AD: Before 

further flight, 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). 

Although the service information specified in 

paragraph (g) of this AD specifies to contact 

Airbus for repair instructions, and specifies 

that action as ‘‘RC’’ (Required for 

Compliance), this AD requires repair as 

specified in this paragraph. Repair of an 

airplane as required by this paragraph does 

not constitute terminating action for the 

repetitive actions required by paragraph (g) of 

this AD, unless specified otherwise in the 

instructions provided by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA. 

(i) 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: 

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. 

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. 

(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 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) of this AD: If 

any service information contains procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or 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 operator’s 

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. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2016–0105, dated 

June 6, 2016, 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– 

2016–9498. 

(2) 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.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

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. 

Issued in Renton, Washington, on 

December 2, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–29676 Filed 12–15–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8428; Directorate 

Identifier 2014–NM–032–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (SNPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposal to supersede Airworthiness 

Directive (AD) 2011–17–09 for all 

Airbus Model A330–200, –200 

Freighter, and –300 series airplanes; and 

AD 2012–25–12 for all Airbus Model 

A330–200 and –300 series airplanes. 

The notice of proposed rulemaking 

(NPRM) proposed to require revising the 

maintenance or inspection program, as 

applicable, to incorporate new or 

revised airworthiness limitation 

requirements. The NPRM was prompted 

by revisions to certain airworthiness 

limitations items (ALI) documents, 

which specify more restrictive 

instructions and/or airworthiness 

limitations. This action revises the 

NPRM by proposing to require revising 

the maintenance or inspection program, 

as applicable, to incorporate more 

restrictive, instructions and/or 

airworthiness limitations that the 

manufacturer has recently issued. We 

are proposing this AD to address the 

unsafe condition on these products. 

DATES: We must receive comments on 

this SNPRM by January 30, 2017. 

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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For Airbus service information 

identified in this SNPRM, contact 


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Airbus 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. 

For Messier-Bugatti-Dowty service 

information identified in this SNPRM, 

contact Messier-Bugatti USA, One 

Carbon Way, Walton, KY 41094; 

telephone 859–525–8583; fax 859–485 

8827; email americascsc@

safranmbd.com. 

You may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

8428; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone: 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, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–8428; Directorate Identifier 

2014–NM–032–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 proposed AD. 

Discussion 

We issued an NPRM to amend 14 CFR 

part 39 to supersede AD 2011–17–09, 

Amendment 39–16773 (76 FR 53305, 

August 26, 2011) (‘‘AD 2011–17–09’’); 

and AD 2012–25–12, Amendment 39– 

17293 (77 FR 75825, December 26, 

2012) (‘‘AD 2012–25–12’’). AD 2011– 

17–09 applies to all Airbus Model 

A330–200 series airplanes, –200 

Freighter, and –300 series airplanes. AD 

2012–25–12 applies to all Airbus Model 

A330–200 and –300 series airplanes. 

The NPRM published in the Federal 

Register on January 13, 2016 (81 FR 

1570) (‘‘the NPRM’’). The NPRM was 

prompted by revisions to certain 

airworthiness limitations items (ALI) 

documents, which specify more 

restrictive instructions and/or 

airworthiness limitations. The NPRM 

proposed to require revising the 

maintenance or inspection program, as 

applicable, to incorporate new or 

revised airworthiness limitation 

requirements. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive, 2014–0009, dated January 8, 

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, –200 Freighter, and 

–300 series airplanes; and Model A340– 

200, –300, –500, and –600 series 

airplanes. The MCAI states: 

The airworthiness limitations for Airbus 

aeroplanes are currently published in 

Airworthiness Limitations Section (ALS) 

documents. 

The instructions and airworthiness 

limitations applicable to the Safe Life 

Airworthiness Limitation Items (SL ALI) are 

given in Airbus A330 ALS Part 1 and A340 

ALS Part 1, which are approved by EASA. 

The revision 07 of Airbus A330 and A340 

ALS Part 1 introduces more restrictive 

instructions and/or airworthiness limitations. 

Failure to comply with this revision could 

result in an unsafe condition. 

For the reason described above, this 

[EASA] AD retains the requirements of EASA 

AD 2012–0179, which is superseded, and 

requires accomplishment of the actions 

specified in Airbus A330 or A340 ALS Part 

1 revision 07. 

In addition, this [EASA] AD also 

supersedes EASA AD 2011–0122–E and 

EASA AD 2011–0212, whose requirements 

have been transferred into Airbus A330 and 

A340 ALS Part 1 revision 07. 

The unsafe condition is fatigue 

cracking, accidental damage, and 

corrosion in certain principal structural 

elements, and possible failure of certain 

life limited parts, which could result in 

reduced structural integrity of the 

airplane. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

8428. 

Actions Since the NPRM Was Issued 

Since we issued the NPRM, Airbus 

has issued Airbus A330 ALS Part 1, Safe 

Life Airworthiness Limitation Items 

(SL–ALI), Revision 08, dated April 11, 

2016, which specifies more restrictive 

instructions and/or airworthiness 

limitations. 

Related Rulemaking 

We are considering similar 

rulemaking for Model A340–200, –300, 

–500, and –600 series airplanes that 

would revise the maintenance or 

inspection program, as applicable, to 

incorporate more restrictive instructions 

and/or airworthiness limitations. 

Currently, there are no U.S.-registered 

Model A340 series airplanes. 

Airworthiness Limitations Based on 

Type Design 

The FAA recently became aware of an 

issue related to the applicability of ADs 

that require incorporation of an ALS 

revision into an operator’s maintenance 

or inspection program. 

Typically, when these types of ADs 

are issued by civil aviation authorities 

of other countries, they apply to all 

airplanes covered under an identified 

type certificate (TC). The corresponding 

FAA AD typically retains applicability 

to all of those airplanes. 

In addition, U.S. operators must 

operate their airplanes in an airworthy 

condition, in accordance with 14 CFR 

91.7(a). Included in this obligation is the 

requirement to perform any 

maintenance or inspections specified in 

the ALS, and in accordance with the 

ALS as specified in 14 CFR 43.16 and 

91.403(c), unless an alternative has been 

approved by the FAA. 

When a TC is issued for a type design, 

the specific ALS, including revisions, is 

a part of that type design, as specified 

in 14 CFR 21.31(c). 

The sum effect of these operational 

and maintenance requirements is an 

obligation to comply with the ALS 

defined in the type design referenced in 

the manufacturer’s conformity 

statement. This obligation may 

introduce a conflict with an AD that 

requires a specific ALS revision if new 

airplanes are delivered with a later 

revision as part of their type design. 


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To address this conflict, the FAA has 

approved alternative methods of 

compliance (AMOCs) that allow 

operators to incorporate the most recent 

ALS revision into their maintenance/ 

inspection programs, in lieu of the ALS 

revision required by the AD. This 

eliminates the conflict and enables the 

operator to comply with both the AD 

and the type design. 

However, compliance with AMOCs is 

normally optional, and we recently 

became aware that some operators 

choose to retain the AD-mandated ALS 

revision in their fleet-wide 

maintenance/inspection programs, 

including those for new airplanes 

delivered with later ALS revisions, to 

help standardize the maintenance of the 

fleet. To ensure that operators comply 

with the applicable ALS revision for 

newly delivered airplanes containing a 

later revision than that specified in an 

AD, we plan to limit the applicability of 

ADs that mandate ALS revisions to 

those airplanes that are subject to an 

earlier revision of the ALS, either as part 

of the type design or as mandated by an 

earlier AD. 

This SNPRM therefore applies to 

Model A330–200, –200 Freighter, and 

–300 series airplanes with an original 

certificate of airworthiness or original 

export certificate of airworthiness that 

was issued on or before the date of 

approval of the ALS revision identified 

in this SNPRM. Operators of airplanes 

with an original certificate of 

airworthiness or original export 

certificate of airworthiness issued after 

that date must comply with the 

airworthiness limitations specified as 

part of the approved type design and 

referenced on the TC data sheet. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Airbus A330 ALS 

Part 1, SL–ALI, Revision 08, dated April 

11, 2016. Messier-Bugatti-Dowty has 

issued Service Letter A33–34 A20, 

Revision 7, including Appendices A 

through F, dated July 20, 2012. This 

service information describes Safe Life 

Airworthiness Limitation Items SL–ALI 

for the landing gear. This service 

information is distinct since it was 

issued by two different manufacturers 

for different purposes. 

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. 

Comments 

We gave the public the opportunity to 

participate in developing this proposed 

AD. We considered the comments 

received. 

Request To Specify New Service 

Information 

Air France requested that we revise 

paragraph (i) of the proposed AD to 

include Messier-Bugatti-Dowty Service 

Letter A33–34 A20, Revision 7, 

including Appendices A through F, 

dated July 20, 2012, as the required 

service information. 

We agree with the commenter’s 

request. The changes in Messier-BugattiDowty Service Letter A33–34 A20, 

Revision 7, including Appendices A 

through F, dated July 20, 2012, do not 

specify additional work. We have 

revised paragraph (i) of this proposed 

AD to specify using Messier-Dowty 

Service Letter A33–34 A20, Revision 5, 

including Appendices A through F, 

dated July 31, 2009; or Messier-BugattiDowty Service Letter A33–34 A20, 

Revision 7, including Appendices A 

through F, dated July 20, 2012. 

Requests To Specify Airbus A330 

Variations 

Air France requested that we revise 

paragraph (k) of the proposed AD to list 

all of the Airbus A330 variations to 

Airbus A330 ALS Part 1, SL–ALS, 

Revision 07, dated September 23, 2013, 

applicable at the effective date of this 

AD. Air France submitted a list of the 

requested variations. 

American Airlines (AAL) requested 

that we add three Airbus A330 

variations to paragraph (k) of the 

proposed AD. AAL stated that the 

NPRM does not include two variation 

documents that AAL currently utilizes 

as part of its approved maintenance 

program. 

We partially agree with the 

commenters’ requests. Airbus has issued 

A330 ALS Part 1, SL–ALI, Revision 08, 

dated April 11, 2016. Therefore, the 

variations for Airbus A330 ALS Part 1, 

SL–ALI, Revision 07, dated September 

23, 2013, are no longer applicable to this 

SNPRM. 

We have changed paragraph (k) of this 

proposed AD to reference Airbus A330 

ALS Part 1, SL–ALI, Revision 08, dated 

April 11, 2016. We have also changed 

paragraph (c) of this proposed AD to 

reference the date of April 11, 2016, for 

the certificate of airworthiness. 

FAA’s Determination and Requirements 

of This SNPRM 

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 proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Certain changes described above 

expand the scope of the NPRM. As a 

result, we have determined that it is 

necessary to reopen the comment period 

to provide additional opportunity for 

the public to comment on this SNPRM. 

This SNPRM would require revisions 

to certain operator maintenance 

documents to include new actions (e.g., 

inspections). Compliance with these 

actions is required by 14 CFR 91.403(c). 

For airplanes that have been previously 

modified, altered, or repaired in the 

areas addressed by this SNPRM, the 

operator may not be able to accomplish 

the actions described in the revisions. In 

this situation, to comply with 14 CFR 

91.403(c), the operator must request 

approval for an AMOC according to 

paragraph (m)(1) of this proposed AD. 

The request should include a 

description of changes to the required 

actions that will ensure the continued 

damage tolerance of the affected 

structure. 

Costs of Compliance 

We estimate that this SNPRM affects 

82 airplanes of U.S. registry. 

The actions that are required by AD 

2011–17–09, and retained in this 

SNPRM, take about 1 work-hour per 

product, at an average labor rate of $85 

per work-hour. Based on these figures, 

the estimated cost of the actions that are 

required by AD 2011–17–09 is $85 per 

product. 

The actions that are required by AD 

2012–25–12, and retained in this 

SNPRM, take about 16 work-hours per 

product (2 main landing gear (MLG) 

bogie beams per airplane), at an average 

labor rate of $85 per work-hour. 

Required parts cost about $255,000 per 

MLG bogie beam. Based on these 

figures, the estimated cost of the actions 

that are required by AD 2012–25–12 is 

up to $256,360 per MLG bogie beam. 

We also estimate that it would take 

about 1 work-hour per product to 

comply with the basic requirements of 

this SNPRM. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of this 

SNPRM on U.S. operators to be $6,970, 

or $85 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 


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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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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) 

2011–17–09, Amendment 39–16773 (76 

FR 53305, August 26, 2011); and AD 

2012–25–12, Amendment 39–17293 (77 

FR 75825, December 26, 2012); and 

adding the following new AD: 

Airbus: Docket No. FAA–2015–8428; 

Directorate Identifier 2014–NM–032–AD. 

(a) Comments Due Date 

We must receive comments by January 30, 

2017. 

(b) Affected ADs 

This AD replaces AD 2011–17–09, 

Amendment 39–16773 (76 FR 53305, August 

26, 2011) (‘‘AD 2011–17–09’’); and AD 2012– 

25–12, Amendment 39–17293 (77 FR 75825, 

December 26, 2012) (‘‘AD 2012–25–12’’). 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1), (c)(2), and 

(c)(3) of this AD, certificated in any category, 

with an original certificate of airworthiness 

or original export certificate of airworthiness 

issued on or before April 11, 2016. 

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

–223, and –243 airplanes. 

(2) Airbus Model A330–223F and –243F 

airplanes. 

(3) Airbus Model A330–301, –302, –303, 

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

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Periodic inspections. 

(e) Reason 

This AD was prompted by revisions to 

certain airworthiness limitations items (ALI) 

documents, which specify more restrictive 

instructions and/or airworthiness limitations. 

We are issuing this AD to detect and correct 

fatigue cracking, accidental damage, or 

corrosion in principal structural elements, 

and possible failure of certain life limited 

parts, which could result in reduced 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Maintenance Program Revision, 

With New Terminating Action 

This paragraph restates the requirements of 

paragraph (h) of AD 2011–17–09, with new 

terminating action. Within 3 months after 

September 30, 2011 (the effective date of AD 

2011–17–09): Revise the maintenance 

program by incorporating Airbus A330 ALS 

Part 1, ‘‘Safe Life Airworthiness Limitation 

Items (SL–ALI), Revision 05, dated July 29, 

2010. Comply with all Airbus A330 ALS Part 

1, SL–ALI, Revision 05, dated July 29, 2010, 

at the times specified therein. Accomplishing 

the actions specified in paragraph (k) of this 

AD terminates the requirements of this 

paragraph. 

(h) Retained Limitation of No Alternative 

Intervals or Limits, With No Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–17–09, with no 

changes. Except as provided by paragraph 

(m) of this AD, after accomplishment of the 

actions specified in paragraph (g) of this AD, 

no alternatives to the maintenance tasks, 

intervals, or limitations specified in 

paragraph (g) of this AD may be used. 

(i) Retained Bogie Beam Replacement, With 

Specific Delegation Approval Language, 

New Terminating Action, and New Service 

Information 

This paragraph restates the requirements of 

paragraph (g) of AD 2012–25–12, with 

specific delegation approval language and 

terminating action and new service 

information. For airplanes identified in 

paragraphs (c)(1) and (c)(3) of this AD: At the 

later of the times specified in paragraphs 

(i)(1) and (i)(2) of this AD, replace all main 

landing gear (MLG) bogie beams having part 

number (P/N) 201485300, 201485301, 

201272302, 201272304, 201272306, or 

201272307, except those that have serial 

number (S/N) S2A, S2B, or S2C, as identified 

in Messier-Dowty Service Letter A33–34 A20, 

Revision 5, including Appendices A through 

F, dated July 31, 2009; or Messier-BugattiDowty Service Letter A33–34 A20, Revision 

7, including Appendices A through F, dated 

July 20, 2012; with a new or serviceable part, 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent). As of the effective date of 

this AD, the applicable MLG bogie beams 

specified in this paragraph must be replaced 

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). Accomplishing the actions 

specified in paragraph (k) of this AD 

terminates the requirements of this 

paragraph. 

(1) At the applicable time specified in 

paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of 

this AD. 

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

–243 series airplanes, weight variant 

(WV)02x, WV05x (except WV058), and 

WV06x series: Before the accumulation of a 

life limit of 50,000 landings or 72,300 total 

flight hours, whichever occurs first from the 

first installation of a MLG bogie beam on the 

airplane. 

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

–243 WV058 series airplanes: Before the 

accumulation of a life limit of 50,000 

landings or 57,900 total flight hours, 

whichever occurs first from the first 

installation of a MLG bogie beam on the 

airplane. 

(iii) For Model A330–301, –302, –303, 

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

airplanes, WV00x, WV01x, WV02x, and 

WV05x series: Before the accumulation of a 

life limit of 46,000 landings or 75,000 total 

flight hours, whichever occurs first from the 

first installation of a MLG bogie beam on the 

airplane. 

(2) Within 6 months after January 30, 2013 

(the effective date of AD 2012–25–12). 

(j) Retained Parts Installation Limitation, 

With New Terminating Action 

This paragraph restates the requirements of 

paragraph (h) of AD 2012–25–12, with new 


asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
91066 Federal Register / Vol. 81, No. 242 / Friday, December 16, 2016 / Proposed Rules 

terminating action. For airplanes identified 

in paragraphs (c)(1) and (c)(3) of this AD, as 

of January 30, 2013 (the effective date of AD 

2012–25–12), a MLG bogie beam having any 

part number identified in paragraph (i) of this 

AD may be installed on an airplane, provided 

its life has not exceeded the life limit 

specified in paragraphs (i)(1)(i), (i)(1)(ii), and 

(i)(1)(iii) of this AD, and is replaced with a 

new or serviceable part before reaching the 

life limit specified in paragraphs (i)(1)(i), 

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

Accomplishing the actions specified in 

paragraph (k) of this AD terminates the 

requirements of this paragraph. 

(k) New Maintenance or Inspection Program 

Revision 

Within 3 months after the effective date of 

this AD: Revise the maintenance or 

inspection program, as applicable, by 

incorporating the information in Airbus A330 

ALS Part 1, SL–ALI, Revision 08, dated April 

11, 2016. The initial compliance times for the 

actions specified in Airbus A330 ALS Part 1, 

SL–ALI, Revision 08, dated April 11, 2016, 

are at the times specified in Airbus A330 

ALS Part 1, SL–ALI, Revision 08, dated April 

11, 2016, or within 3 months after the 

effective date of this AD, whichever occurs 

later. Accomplishing the actions specified in 

this paragraph terminates the requirements 

specified in paragraphs (g) through (j) of this 

AD. 

(l) New Limitation of No Alternative Actions 

or Intervals 

After the maintenance or inspection 

program, as applicable, has been revised, as 

required by paragraph (k) of this AD, no 

alternative actions (e.g., inspections) or 

intervals may be used unless the actions or 

intervals are approved as an AMOC in 

accordance with the procedures specified in 

paragraph (m)(1) of this AD. 

(m) 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: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(n) Related Information 

(1) For Airbus 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. 

(2) For Messier-Bugatti-Dowty service 

information identified in this AD, contact 

Messier-Bugatti USA, One Carbon Way. 

Walton, KY 41094; telephone 859–525–8583; 

fax 859–485 8827; email americascsc@

safranmbd.com. 

(3) 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. 

Issued in Renton, Washington, on 

November 22, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–28802 Filed 12–15–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9439; Directorate 

Identifier 2016–NM–170–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 787–8 

airplanes. This proposed AD was 

prompted by a report indicating that 

during an airplane inspection in 

production, the variable frequency 

starter generator (VFSG) power feeder 

cables were found to contain terminal 

lugs incorrectly installed common to 

terminal blocks located in the wing 

front spar. This proposed AD would 

require a general visual inspection of 

the wings, section 16, terminal lugs at 

the terminal power block of the VFSG 

power feeder cable for correct 

installation and if required, applicable 

corrective actions. We are proposing 

this AD to address the unsafe condition 

on these products. 

DATES: We must receive comments on 

this proposed AD by January 30, 2017. 

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 NPRM, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster 

Blvd., MC 110–SK57, Seal Beach, CA 

90740–5600; telephone: 562–797–1717; 

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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

9439. 

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–2016– 

9439; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket 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: 

Brendan Shanley, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office (ACO), 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425– 

917–6492; fax: 425–917–6590; email: 

brendan.shanley@faa.gov. 

SUPPLEMENTARY INFORMATION: 


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