69846 Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations 

and (i) of AD 2013–09–01, Amendment 39– 

17442 (78 FR 27001, May 9, 2013), for the 

replaced skin panel only. 

(r) Exceptions to Service Information 

Specifications 

(1) Where Boeing Service Bulletin 737– 

53A1177, Revision 7, dated June 14, 2013, 

specifies a compliance time ‘‘after the 

Revision 7 date of this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where Boeing Service Bulletin 737– 

53A1177, Revision 6, dated May 31, 2001; 

and Boeing Service Bulletin 737–53A1177, 

Revision 7, dated June 14, 2013; specify to 

contact Boeing for certain procedures: Do the 

specified actions before further flight using a 

method approved in accordance with the 

procedures specified in paragraph (t) of this 

AD. 

(3) Where Boeing Service Bulletin 737– 

53A1177, Revision 6, dated May 31, 2001; 

and Boeing Service Bulletin 737–53A1177, 

Revision 7, dated June 14, 2013; include the 

phrase ‘‘or is Boeing or FAA approved,’’ this 

AD requires the ‘‘Boeing Approval’’ to be 

requested in accordance with the procedures 

specified in paragraph (t) of this AD. 

(s) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using the applicable 

service information specified in paragraphs 

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

which were incorporated by reference in AD 

2002–07–08, Amendment 39–12702 (67 FR 

17917, April 12, 2002). 

(i) Boeing Service Bulletin 737–53A1177, 

Revision 4, dated September 2, 1999. 

(ii) Boeing Service Bulletin 737–53A1177, 

Revision 5, dated February 15, 2001, which 

continues to be incorporated by reference in 

this AD. 

(iii) Boeing Service Bulletin 737–53A1177, 

Revision 6, dated May 31, 2001, which 

continues to be incorporated by reference in 

this AD. 

(2) This paragraph provides credit for the 

actions required by paragraphs (i) through (o) 

of this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Service Bulletin 737–53A1177, 

Revision 6, dated May 31, 2001, which was 

incorporated by reference in AD 2002–07–08, 

Amendment 39–12702 (67 FR 17917, April 

12, 2002) and continues to be incorporated 

by reference in this AD. 

(t) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 (u)(1) of this AD. Information may 

be emailed to: 9-ANM-LAACO-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, Los Angeles 

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. 

(4) AMOCs approved for AD 2002–07–08, 

Amendment 39–12702 (67 FR 17917, April 

12, 2002), are approved as AMOCs for the 

corresponding provisions of this AD. 

(u) Related Information 

(1) For more information about this AD, 

contact Jennifer Tsakoumakis, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles Aircraft Certification 

Office (ACO), 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5264; fax: 562–627–5210; email: 

Jennifer.Tsakoumakis@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(v) 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) Boeing Service Bulletin 737–53A1177, 

Revision 7, dated June 14, 2013. 

(ii) Reserved. 

(3) The following service information was 

approved for IBR on May 17, 2002 (67 FR 

17917, April 12, 2002). 

(i) Boeing Service Bulletin 737–53A1177, 

Revision 5, dated February 15, 2001. 

(ii) Boeing Service Bulletin 737–53A1177, 

Revision 6, dated May 31, 2001. 

(4) For Boeing 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. 

(5) 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. 

(6) 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 October 

11, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–26616 Filed 11–10–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2461; Directorate 

Identifier 2013–NM–202–AD; Amendment 

39–18310; AD 2015–22–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2009–18– 

15, for all Airbus Model A300, A310, 

and A300 B4–600, B4–600R, and F4– 

600R series airplanes, and Model A300 

C4–605R Variant F airplanes 

(collectively called Model A300–600 

series airplanes). AD 2009–18–15 

required revising the Airworthiness 

Limitations section (ALS) of the 

Instructions for Continued 

Airworthiness (ICA) to require 

additional life limits and/or 

replacements for certain main landing 

gear and nose landing gear components. 

This new AD requires revising the 

maintenance or inspection program to 

incorporate new maintenance 

requirements and airworthiness 

limitations. This AD was prompted by 

a determination that existing 

maintenance requirements and 

airworthiness limitations are inadequate 

to ensure the structural integrity of the 

airplane. We are issuing this AD to 

prevent failure of certain system 

components, which could result in 

reduced structural integrity of the 

airplane. 

DATES: This AD becomes effective 

December 17, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 17, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of October 27, 2009 (74 FR 

48143, September 22, 2009). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

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Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations 69847 

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

FAA-2015-2461; or in person at the 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC. 

For service information identified in 

this AD, contact Airbus SAS, 

Airworthiness Office—EAW, 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. For information on 

the availability of this material at the 

FAA, call 425–227–1221. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

2461. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2009–18–15, 

Amendment 39–16011 (74 FR 48143, 

September 22, 2009). AD 2009–18–15 

applied to all Airbus Model A300, 

A310, and A300 B4–600, B4–600R, and 

F4–600R series airplanes; and Model 

A300 C4–605R Variant F airplanes 

(collectively called Model A300–600 

series airplanes). The NPRM published 

in the Federal Register on July 14, 2015 

(80 FR 40942). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0248, dated October 14, 

2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for all Model A300, 

A310, and A300–600 series airplanes. 

The MCAI states: 

The airworthiness limitations for Airbus 

aeroplanes are currently published in 

Airworthiness Limitations Section (ALS) 

documents. 

The mandatory instructions and 

airworthiness limitations applicable to the 

Aging Systems Maintenance (ASM) are 

specified in Airbus A310 or A300–600 ALS 

Part 4 documents, which are approved by the 

European Aviation Safety Agency (EASA). 

EASA AD 2007–0092 [http://

ad.easa.europa.eu/blob/easa_ad_2007_

0092.pdf/AD_2007-0092] [which corresponds 

to FAA AD 2009–06–06, Amendment 39– 

15842 (74 FR 12228, March 24, 2009)] was 

issued to require compliance to the 

requirements as specified in these 

documents. 

The revision 02 of Airbus A310 and Airbus 

A300–600 ALS Part 4 documents introduces 

more restrictive maintenance requirements 

and/or airworthiness limitations. Failure to 

comply with the instructions of ALS Part 4 

could result in an unsafe condition [reduced 

structural integrity of the airplane.] 

For the reasons described above, this new 

[EASA] AD retains the requirements of EASA 

AD 2007–0092, which is superseded, and 

requires the implementation of the new or 

more restrictive maintenance requirements 

and/or airworthiness limitations as specified 

in Airbus A310 ALS Part 4, Revision 02, or 

Airbus A300–600 ALS Part 4, Revision 02, as 

applicable to aeroplane type/model. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/#!document

Detail;D=FAA-2015-2461-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 40942, July 14, 2015) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data 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 (80 FR 

40942, July 14, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 40942, 

July 14, 2015). 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. ‘‘Sub-part 1–2: Life 

Limits’’ and ‘‘Sub-part 1–3: 

Demonstrated fatigue lives’’ of Part 1, 

‘‘Safe Life Airworthiness Limitation 

Items,’’ in each of these documents 

describe procedures for revising the 

maintenance or inspection program to 

incorporate new maintenance 

requirements and airworthiness 

limitations. 

• For Model A300 series airplanes: 

Part 1, ‘‘Safe Life Airworthiness 

Limitation Items,’’ Revision 01, dated 

September 5, 2013, of the Airbus Model 

A300 Airworthiness Limitations 

Section. 

• For Model A300 B4–600, B4–600R, 

and F4–600R series airplanes, and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes): Part 1, ‘‘Safe 

Life Airworthiness Limitation Items,’’ 

Revision 01, dated September 5, 2013, 

of the Airbus Model A300–600 

Airworthiness Limitations Section. 

• For Model A310 series airplanes: 

Part 1, ‘‘Safe Life Airworthiness 

Limitation Items,’’ Revision 01, dated 

September 5, 2013, of the Airbus Model 

A310 Airworthiness Limitations 

Section. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business, or by the means 

identified in the ADDRESSES section of 

this AD. 

Costs of Compliance 

We estimate that this AD affects 177 

airplanes of U.S. registry. 

The retained ALS revision required by 

AD 2009–18–15, Amendment 39–16011 

(74 FR 48143, September 22, 2009), 

takes about 1 work-hour per product, at 

an average labor rate of $85 per workhour. Based on these figures, the 

estimated cost of the actions that were 

required by AD 2009–18–15 is $85 per 

product. 

We also estimate that it takes about 1 

work-hour per product to comply with 

the new ALS revision of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD on U.S. operators to be 

$15,045, 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, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

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69848 Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/#!docket

Detail;D=FAA-2015-2461; or in person 

at the Docket Management Facility 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive AD 

2009–18–15, Amendment 39–16011 (74 

FR 48143, September 22, 2009), and 

adding the following new AD: 

2015–22–05 Airbus: Amendment 39–18310. 

Docket No. FAA–2015–2461; Directorate 

Identifier 2013–NM–202–AD. 

(a) Effective Date 

This AD becomes effective December 17, 

2015. 

(b) Affected ADs 

(1) This AD replaces AD 2009–18–15, 

Amendment 39–16011 (74 FR 48143, 

September 22, 2009). 

(2) Accomplishing certain requirements of 

paragraph (g) of this AD satisfies the 

requirements of paragraph A. of AD 84–02– 

04, Amendment 39–4795 (49 FR 2746, 

January 23, 1984). 

(c) Applicability 

This AD applies to Airbus Model A300 B2– 

1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, 

and B4–203 airplanes; Model A300 B4–601, 

B4–603, B4–620, and B4–622 airplanes; 

Model A300 B4–605R and B4–622R 

airplanes; Model A300 F4–605R and F4– 

622R, and A300 C4–605R Variant F 

airplanes; and Model A310–203, –204, –221, 

–222, –304, –322, –324, and –325 airplanes; 

certificated in any category, all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America 32, Landing Gear. 

(e) Reason 

This AD was prompted by a determination 

that existing maintenance requirements and 

airworthiness limitations are inadequate to 

ensure the structural integrity of the airplane. 

We are issuing this AD to prevent failure of 

certain system components, 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 Revision of Airworthiness 

Limitation Section (ALS) 

This paragraph restates the requirements of 

paragraph (h) of AD 2009–18–15, 

Amendment 39–16011 (74 FR 48143, 

September 22, 2009). For Model A300, A310, 

and A300–600 series airplanes: Within 3 

months after October 27, 2009 (the effective 

date of AD 2009–18–15), revise the ALS of 

the instructions for continued airworthiness 

(ICA) to incorporate the applicable document 

listed in paragraph (g)(1), (g)(2), or (g)(3) of 

this AD. Accomplishing the actions specified 

in the applicable document satisfies the 

requirements of paragraph A. of AD 84–02– 

04, Amendment 39–4795 (49 FR 2746, 

January 23, 1984). 

(1) For Model A300 series airplanes: 

Incorporate the applicable document listed in 

paragraph (g)(1)(i) or (g)(1)(ii) of this AD. 

(i) Section 05–10–00, Revision 28, dated 

February 27, 1998, of Chapter 05, ‘‘Service 

Life Limits and Maintenance Checks,’’ of the 

Airbus A300 Aircraft Maintenance Manual, 

except that the parts listed in table 1 to 

paragraph (g) of this AD are subject to the life 

limits defined in the document listed in 

paragraph (g)(1)(ii) of this AD. 

(ii) ‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Subpart 1–3: Demonstrated Fatigue Lives’’ of Part 

1, ‘‘Safe Life Airworthiness Limitation 

Items,’’ dated September 6, 2007, of the 

Airbus A300 ALS. 

TABLE 1 TO PARAGRAPH (g) OF THIS

AD—PARTS SUBJECT TO THE LIFE

LIMITS SPECIFIED IN THE DOCUMENT

IDENTIFIED IN PARAGRAPH (g)(1)(ii) 

OF THIS AD 

Part No. 

(P/N) Part name 

P/N C61643–2, P/N 

C61643–4, P/N 

C61643–5.

Main landing gear 

(MLG) shock absorber end fitting. 

P/N A32210001205xx Nose landing gear 

(NLG) pintle pin. 

P/N C62037–1 .......... NLG shock absorber 

bottom. 

P/N 196–0328–501 ... Cross beam (Pratt & 

Whitney forward 

engine mount). 

(2) For Model A310 series airplanes: 

Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and 

‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’ 

of Part 1, ‘‘Safe Life Airworthiness Limitation 

Items,’’ dated December 21, 2006, of the 

Airbus A310 ALS. 

(3) For Model A300 B4–600, B4–600R, and 

F4–600R series airplanes, and Model A300 

C4–605R Variant F airplanes (collectively 

called Model A300–600 series airplanes): 

Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and 

‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’ 

of Part 1, ‘‘Safe Life Airworthiness Limitation 

Items,’’ dated December 21, 2006, of the 

Airbus A300–600 ALS. 

(h) Retained Initial Compliance Times and 

Repetitive Inspections 

This paragraph restates the requirements of 

paragraph (i) of AD 2009–18–15, Amendment 

39–16011 (74 FR 48143, September 22, 2009). 

Do the replacement at the applicable time 

specified in paragraph (h)(1) or (h)(2) of this 

AD, except as provided by paragraph (i) of 

this AD. The replacement must be done 

thereafter within the interval specified in the 

applicable document identified in paragraph 

(g)(1), (g)(2), or (g)(3) of this AD. 

(1) For any life limitation/task that has 

been complied with before October 27, 2009 

(the effective date of AD 2009–18–15, 

Amendment 39–16011), in accordance with 

the applicable document listed in paragraph 

(g)(1), (g)(2), or (g)(3) of this AD, or in 

accordance with paragraph (g) of AD 2009– 

18–15, use the last accomplishment of each 

limitation/task as a starting point for 

accomplishing each corresponding 

limitation/task required by this AD. 

(2) For any life limitation/task that has not 

been complied with before October 27, 2009 

(the effective date of AD 2009–18–15, 

Amendment 39–16011), in accordance with 

the applicable document listed in paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD, or in 

accordance with paragraph (g) of AD 2009– 

18–15, the initial compliance time starts from 

the date of initial entry into service as 

defined in the applicable document. 

(i) Retained Special Compliance Times 

This paragraph restates the requirements of 

paragraph (j) of AD 2009–18–15, Amendment 

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Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations 69849 

39–16011 (74 FR 48143, September 22, 2009). 

For any airplane on which the history of 

accumulated landings is partial or unknown, 

or where the history of application details 

(airplane type, model, weight variant, etc.) is 

partial or unknown: Parts listed in figure 1 

to paragraph (i) of this AD must be replaced 

at the associated compliance time. The 

replacement must be done thereafter at the 

interval specified in the applicable 

document(s) specified in paragraphs (g)(1), 

(g)(2), and (g)(3) of this AD. 

Note 1 to paragraph (i) of this AD: Airbus 

Service Information Letter 32–118, Revision 

02, dated October 24, 2007, provides 

operators with guidance on the means to 

assign a conservative calculated life to parts 

whose history of accumulated landings is 

partial or unknown; and to select the 

limitations applicable to parts whose history 

of application details (aircraft type, aircraft 

model, weight variant, etc.) is partial or 

unknown. 

FIGURE 1 TO PARAGRAPH (i) OF THIS AD—SPECIAL COMPLIANCE TIMES

Designation 

Aircraft type applicability 

Start date 

Compliance time 

(whichever occurs first 

A300 A310 A300–600 after the ‘‘start date’’) 

P/N 

Landings Calendar 

time X X X 

MAIN LANDING GEAR 

Aft pintle pin ................. A32140032200xx ......... X .................. .................. December 13, 2007 ..... 13,500 9 years. 

A32140056200xx ......... X .................. .................. December 13, 2007 ..... 13,500 9 years. 

A32140056202xx ......... X .................. .................. December 13, 2007 ..... 13,500 9 years. 

A32140057200xx ......... X .................. .................. December 13, 2007 ..... 13,500 9 years. 

A32140057202xx ......... X .................. X December 13, 2007 ..... 13,500 9 years. 

A32140062000xx ......... X .................. .................. December 13, 2007 ..... 13,500 9 years. 

A32140063000xx ......... X .................. X December 13, 2007 ..... 13,500 9 years. 

Half ball housing (Fwd 

pintle bearing).

A32140036200xx .........

A32140036202xx .........

X 

X 

..................

..................

..................

..................

December 13, 2007 .....

December 13, 2007 .....

13,500 

13,500 

9 years. 

9 years. 

A32140036204xx ......... X .................. .................. December 13, 2007 ..... 13,500 9 years. 

A32140036206xx ......... X .................. .................. December 13, 2007 ..... 13,500 9 years. 

A32140042200xx ......... X .................. X December 13, 2007 ..... 13,500 9 years. 

A32140042202xx ......... X .................. X December 13, 2007 ..... 13,500 9 years. 

A32140068002xx ......... X .................. .................. December 13, 2007 ..... 13,500 9 years. 

A32140068004xx ......... X .................. .................. December 13, 2007 ..... 13,500 9 years. 

A32140069002xx ......... X .................. X December 13, 2007 ..... 13,500 9 years. 

A32140069004xx ......... X .................. X December 13, 2007 ..... 13,500 9 years. 

Ball (Fwd pintle pin) ..... A32140012202xx ......... X .................. .................. December 13, 2007 ..... 13,500 9 years. 

A32140043202xx ......... X .................. X December 13, 2007 ..... 13,500 9 years. 

Pin (Multiple link/Frame 

50).

A53833451200xx .........

A53833451206xx .........

X 

X 

..................

..................

..................

..................

December 13, 2007 .....

December 13, 2007 .....

13,500 

13,500 

9 years. 

9 years. 

A53834451200xx ......... X .................. .................. December 13, 2007 ..... 13,500 9 years. 

A53834451202xx ......... X .................. X April 25, 2007 .............. 13,500 9 years. 

Pin (Drop link/Frame 

50).

A53811122200xx ......... .................. X .................. April 25, 2007 .............. 18,000 9 years. 

MLG Barrel Assembly 

Upper torque link pin 

nut.

00–200–402 .................

SL40089 ......................

X 

X 

..................

..................

..................

..................

December 13, 2007 .....

December 13, 2007 .....

N/A 

N/A 

30 months. 

30 months. 

SL40089P .................... X .................. .................. December 13, 2007 ..... N/A 30 months. 

SL40123 ...................... X .................. .................. December 13, 2007 ..... N/A 30 months. 

SL40123P .................... X X X April 25, 2007 .............. N/A 30 months. 

Torque link medium pin 

nut.

00–200–358 .................

SL40114P ....................

X 

X 

..................

X 

..................

..................

December 13, 2007 .....

April 25, 2007 ..............

N/A 

N/A 

30 months. 

30 months. 

SL40132 ...................... X .................. .................. December 13, 2007 ..... N/A 30 months. 

SL40132P .................... X .................. X April 25, 2007 .............. N/A 30 months. 

Attaching fitting pin ....... C62311–1 .................... X .................. .................. December 13, 2007 ..... 13,500 9 years. 

C62311–20 .................. X .................. X April 25, 2007 .............. 13,500 9 years. 

Pin (Connecting rod/

Upper rod).

C65815 ........................

C65815–1 ....................

X 

X 

..................

..................

..................

..................

December 13, 2007 .....

December 13, 2007 .....

13,500 

13,500 

9 years. 

9 years. 

C65815–20 .................. X .................. .................. December 13, 2007 ..... 13,500 9 years. 

C66472 ........................ X .................. .................. December 13, 2007 ..... 13,500 9 years. 

C66472–1 .................... X .................. .................. December 13, 2007 ..... 13,500 9 years. 

C66472–20 .................. X .................. X April 25, 2007 .............. 13,500 9 years. 

D52751 ........................ .................. X .................. April 25, 2007 .............. 18,000 9 years. 

MLG Shock Absorber Assembly 

Lower torque link pin 

nut.

00–200–402 .................

SL40089 ......................

X 

X 

..................

..................

..................

..................

December 13, 2007 .....

December 13, 2007 .....

N/A 

N/A 

30 months. 

30 months. 

SL40089P .................... X .................. .................. December 13, 2007 ..... N/A 30 months. 

SL40123 ...................... X .................. .................. December 13, 2007 ..... N/A 30 months. 

SL40123P .................... X X X April 25, 2007 .............. N/A 30 months. 

mstockstill on DSK4VPTVN1PROD with RULES

69850 Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations 

FIGURE 1 TO PARAGRAPH (i) OF THIS AD—SPECIAL COMPLIANCE TIMES—Continued 

Designation 

Aircraft type applicability 

Start date 

Compliance time 

(whichever occurs first 

A300 A310 A300–600 after the ‘‘start date’’) 

P/N 

Landings Calendar 

time X X X 

Bogie beam pivot pin 

nut.

SL40054 ...................... X .................. .................. December 13, 2007 ..... at next removal/

installation.1 2

SL40054P .................... X .................. X April 25, 2007 .............. at next removal/

installation.1 2

SL40413P .................... .................. X .................. April 25, 2007 .............. at next removal/

installation.1 2

MLG Lock Link Assembly 

Lock link medium pin ... C61485–1 .................... X .................. .................. December 13, 2007 ..... N/A 30 months. 

C61485–20 .................. X .................. X April 25, 2007 .............. N/A 30 months. 

NOSE LANDING GEAR 

Pintle pin ....................... A32210079200xx ......... X X X April 25, 2007 .............. 13,500 9 years. 

NLG Telescopic Strut Assembly 

Nut (Cylinder/Locking 

cylinder).

C61375 ........................

D55955 ........................

X 

X 

X 

X 

..................

X 

April 25, 2007 ..............

April 25, 2007 ..............

13,500 

13,500 

9 years. 

9 years. 

Locking sleeve .............. C61389 ........................ X X .................. December 13, 2007 ..... 13,200 9 years. 

C61389–1 .................... X X X April 25, 2007 .............. 13,500 9 years. 

NLG Barrel Assembly 

Pin (Clevis/Telescopic 

strut).

C62231–1 ....................

C62231–2 ....................

X 

X 

..................

..................

..................

..................

December 13, 2007 .....

December 13, 2007 .....

13,200 

13,200 

9 years. 

9 years. 

C62231–20 .................. X X X April 25, 2007 .............. 13,500 9 years. 

D56530 ........................ X X X April 25, 2007 .............. 13,500 9 years. 

Lower pin (Link/Clevis) C62268–1 .................... X .................. .................. December 13, 2007 ..... 13,200 9 years. 

C62268–2 .................... X .................. .................. December 13, 2007 ..... 13,200 9 years. 

C62268–20 .................. X X X April 25, 2007 .............. 13,500 9 years. 

Link (Clevis/Barrel) ....... C62230–1 .................... X X X April 25, 2007 .............. 13,500 9 years. 

D56526 ........................ X X X April 25, 2007 .............. 13,500 9 years. 

Upper pin (Link/Barrel) C62267–1 .................... X .................. .................. December 13, 2007 ..... 13,200 9 years. 

C62267–2 .................... X .................. .................. December 13, 2007 ..... 13,200 9 years. 

C62267–20 .................. X X X April 25, 2007 .............. 13,500 9 years. 

End fitting pin nut ......... D68062 ........................ X X X December 13, 2007 ..... at next removal/

installation.2

MS17825–6 ................. X X X December 13, 2007 ..... at next removal/

installation.2

End fitting pin ............... AN6–17 ........................ X X X December 13, 2007 ..... at next removal/

installation.2

D61183 ........................ X X X December 13, 2007 ..... at next removal/

installation.2

D68063 ........................ X X X December 13, 2007 ..... at next removal/

installation.2

NAS1306–22D ............. X X X December 13, 2007 ..... at next removal/

installation.2

End fitting ..................... C62032 ........................ X X X April 25, 2007 .............. 13,500 9 years. 

C62032–1 .................... X X X April 25, 2007 .............. 13,500 9 years. 

Rack ............................. C61453 ........................ X .................. .................. December 13, 2007 ..... 13,200 9 years. 

C61453–1 .................... X X X April 25, 2007 .............. 13,500 9 years. 

C61453–20 .................. X X X April 25, 2007 .............. 13,500 9 years. 

C61453–40 .................. X X X April 25, 2007 .............. 13,500 9 years. 

C61453–41 .................. X X X April 25, 2007 .............. 13,500 9 years. 

Torque link pin (Upper 

& Lower).

C62223–1 ....................

C62223–20 ..................

X 

X 

..................

X 

..................

X 

December 13, 2007 .....

April 25, 2007 ..............

13,200 

13,500 

9 years. 

9 years. 

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Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations 69851 

FIGURE 1 TO PARAGRAPH (i) OF THIS AD—SPECIAL COMPLIANCE TIMES—Continued 

Designation 

Aircraft type applicability 

Start date 

Compliance time 

(whichever occurs first 

A300 A310 A300–600 after the ‘‘start date’’) 

P/N 

Landings Calendar 

time X X X 

Torque link medium pin 

nut.

SL40110P .................... X X X April 25, 2007 .............. N/A 30 months. 

NLG Shock Absorber Assembly 

Wheel axle nut ............. C62879 ........................ X X X April 25, 2007 .............. 4,000 24 months. 

Upper cam dowel ......... C62270 ........................ X X X December 13, 2007 ..... at next removal/

installation. 

Upper cam .................... C62034–1 .................... X X X April 25, 2007 .............. 13,500 9 years. 

Lower cam .................... C62035 ........................ X X X April 25, 2007 .............. 13,500 9 years. 

Restrictor ...................... C62036 ........................ X .................. .................. December 13, 2007 ..... 13,200 9 years. 

C62036–1 .................... X .................. .................. December 13, 2007 ..... 13,200 9 years. 

C62036–2 .................... X .................. .................. December 13, 2007 ..... 13,200 9 years. 

C67863 ........................ X .................. .................. December 13, 2007 ..... 13,200 9 years. 

C67863–1 .................... X X X April 25, 2007 .............. 13,500 9 years. 

C67863–2 .................... X X X April 25, 2007 .............. 13,500 9 years. 

C67863–3 .................... X .................. .................. December 13, 2007 ..... 13,500 9 years. 

C67863–4 .................... X X X April 25, 2007 .............. 13,500 9 years. 

Lower cam dowel ......... C62866 ........................ X X X December 13, 2007 ..... at next removal/

installation.2

Nut (S/A/Barrel) ............ C64040 ........................ X .................. .................. December 13, 2007 ..... at next removal/

installation.1 2

C64040–1 .................... X X X December 13, 2007 ..... at next removal/

installation.1 2

1When the nut is temporarily removed and reinstalled for the purpose of performing maintenance outside a workshop, no replacement is required provided the nut’s removal and reinstallation are performed on the same assembly and neither the assembly nor the nut accumulates time 

in service during the period between the removal and reinstallation. 2 If the removal/installation was done after the start date, but before the effective date of this AD, the compliance time is within 3 months after 

October 27, 2009 (the effective date of AD 2009–18–15, Amendment 39–16011 (74 FR 48143, September 22, 2009)). 

(j) New Requirements of This AD: 

Maintenance Program Revision 

Within 3 months after the effective date of 

this AD: Revise the maintenance or 

inspection program, as applicable, to 

incorporate the applicable limitation, 

replacement, or inspection specified in 

paragraph (j)(1), (j)(2), or (j)(3) of this AD, as 

applicable. Doing any task required by this 

paragraph terminates the corresponding task 

required by paragraph (g), (h), and (i) of this 

AD. 

(1) For Model A300 series airplanes: 

Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and 

‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’ 

of Part 1, ‘‘Safe Life Airworthiness Limitation 

Items,’’ Revision 01, dated September 5, 

2013, of the Airbus A300 ALS. 

(2) For Model A300 B4–600, B4–600R, and 

F4–600R series airplanes, and Model A300 

C4 605R Variant F airplanes (collectively 

called Model A300–600 series airplanes): 

Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and 

‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’ 

of Part 1, ‘‘Safe Life Airworthiness Limitation 

Items,’’ Revision 01, dated September 5, 

2013, of the Airbus A300–600 ALS. 

(3) For Model A310 series airplanes: 

Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and 

‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’ 

of Part 1, ‘‘Safe Life Airworthiness Limitation 

Items,’’ dated Revision 01, September 5, 

2013, of the Airbus A310 ALS. 

(k) New Limitation: No Alternative Actions 

or Intervals 

After accomplishment of the revision 

required by paragraph (j) of this AD, no 

alternative actions (e.g., inspections) or 

intervals may be used unless the actions or 

intervals are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (l) of this AD. 

(l) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; 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 European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0248, dated 

October 14, 2013, 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–2015–2461–0002. 

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69852 Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD 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 this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on November 27, 2015. 

(i) ALS Part 1, ‘‘Safe Life Airworthiness 

Limitation Items,’’ Revision 01, dated 

September 5, 2013, of the Airbus Model A300 

Airworthiness Limitations Section. 

(ii) ALS Part 1, ‘‘Safe Life Airworthiness 

Limitation Items,’’ Revision 01, dated 

September 5, 2013, of the Airbus Model 

A300–600 Airworthiness Limitations 

Section. 

(iii) ALS Part 1, ‘‘Safe Life Airworthiness 

Limitation Items,’’ Revision 01, dated 

September 5, 2013, of the Airbus Model A310 

Airworthiness Limitations Section. 

(4) The following service information was 

approved for IBR on October 27, 2009 (74 FR 

48143, September 22, 2009). 

(i) Section 05–10–00 of Chapter 05, 

‘‘Service Life Limits and Maintenance 

Checks,’’ of the Airbus A300 Aircraft 

Maintenance Manual (AMM), Revision 28, 

dated February 27, 1998. 

(A) The AMM title page; the Record of 

Revisions, Effective Pages, and Table of 

Content pages; and Section 05–10–00; for 

Chapter 05 of Airbus A300 AMM are all 

dated February 27, 1998. 

(B) The revision level of Chapter 05 of the 

Airbus A300 AMM is indicated only in the 

Record of Revisions section of Chapter 05. 

(C) The List of Effective Pages (LOEP) for 

Chapter 05 of the Airbus A300 AMM 

contains the discrepancies identified in 

paragraphs (n)(4)(i)(C)(1) through 

(n)(4)(i)(C)(4) of this AD. 

(1) The Transmittal Letter page, page 4 of 

the LOEP and Table of Contents sections, 

page 2 of Subsection 05–00–01, Subsection 

05–10–00, and page 1 of Subsection 05–11– 

11, are not listed in the LOEP for Chapter 05 

of the Airbus A300 AMM. 

(2) The LOEP for Chapter 05 of the Airbus 

A300 AMM does not specify a date for the 

Record of Revisions page. 

(3) The LOEP for Chapter 05 of the Airbus 

A300 AMM identifies three pages for 

Subsection 05–11–00, Configuration 5; 

however, only one page exists. 

(4) The LOEP for Chapter 05 of the Airbus 

A300 AMM identifies three pages for 

Subsection 05–11–00, Configuration 9; 

however, those pages do not exist. 

(ii) Airbus A300 Airworthiness Limitations 

Section, ALS Part 1, ‘‘Safe Life Airworthiness 

Limitations Items’’ dated September 6, 2007. 

(iii) Airbus A300–600 Airworthiness 

Limitations Section, ALS Part 1, ‘‘Safe Life 

Airworthiness Limitations Items’’ dated 

December 21, 2006. 

(iv) Airbus A310 Airworthiness 

Limitations Section, ALS Part 1, ‘‘Safe Life 

Airworthiness Limitation Items’’ dated 

December 21, 2006. 

(5) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 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. 

(6) 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. 

(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 October 

21, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–27449 Filed 11–10–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

Bureau of Industry and Security 

15 CFR Part 744 

[Docket No. 150911846–5846–01] 

RIN 0694–AG74 

Addition of Certain Persons and 

Modification of Certain Entries to the 

Entity List; and Removal of Certain 

Persons From the Entity List 

AGENCY: Bureau of Industry and 

Security, Commerce. 

ACTION: Final rule. 

SUMMARY: This rule amends the Export 

Administration Regulations (EAR) by 

adding seven persons under ten entries 

to the Entity List. The seven persons 

who are added to the Entity List have 

been determined by the U.S. 

Government to be acting contrary to the 

national security or foreign policy 

interests of the United States. These 

persons will be listed on the Entity List 

under the destinations of China and 

Hong Kong. 

This final rule also removes two 

persons from the Entity List. One entity 

requested removal from the Entity List 

in accordance with the procedure for 

requesting removal or modification of 

an Entity List entity. The End-User 

Review Committee (ERC) decided to 

remove this entity following a review of 

information provided in the removal 

request. The ERC decided to remove a 

second person from the Entity List 

following a proposal submitted by an 

ERC member agency, in accordance 

with the procedure for requesting 

removal or modification of an Entity 

List entity. 

Finally, this final rule modifies ten 

existing entries on the Entity List 

consisting of one entry under China and 

nine entries under Hong Kong to 

provide additional or modified 

addresses and/or aliases for these 

persons. 

DATES: This rule is effective on 

November 12, 2015. 

FOR FURTHER INFORMATION CONTACT: 

Chair, End-User Review Committee, 

Office of the Assistant Secretary, Export 

Administration, Bureau of Industry and 

Security, Department of Commerce, 

Phone: (202) 482–5991, Fax: (202) 482– 

3911, Email: ERC@bis.doc.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The Entity List (Supplement No. 4 to 

Part 744) identifies entities and other 

persons reasonably believed to be 

involved, or to pose a significant risk of 

being or becoming involved, in 

activities contrary to the national 

security or foreign policy interests of the 

United States. The EAR imposes 

additional license requirements on, and 

limits the availability of most license 

exceptions for, exports, reexports, and 

transfers (in-country) to those listed. 

The ‘‘license review policy’’ for each 

listed entity or other person is identified 

in the License Review Policy column on 

the Entity List and the impact on the 

availability of license exceptions is 

described in the Federal Register notice 

adding entities or other persons to the 

Entity List. BIS places entities and other 

persons on the Entity List pursuant to 

sections of part 744 (Control Policy: 

End-User and End-Use Based) and part 

746 (Embargoes and Other Special 

Controls) of the EAR. 

The ERC, composed of representatives 

of the Departments of Commerce 

(Chair), State, Defense, Energy and, 

where appropriate, the Treasury, makes 

all decisions regarding additions to, 

removals from, or other modifications to 

the Entity List. The ERC makes all 

decisions to add an entry to the Entity 

List by majority vote and all decisions 

to remove or modify an entry by 

unanimous vote. 

ERC Entity List Decisions 

Additions to the Entity List 

This rule implements the decision of 

the ERC to add seven persons under ten 

entries to the Entity List. These seven 

persons are being added on the basis of 

mstockstill on DSK4VPTVN1PROD with RULES