## 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://


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

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, atan 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.


## 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 

### P ARAGRAPH 

### (g) OF 

### T HIS



### AD—P ARTS 

### S UBJECT TO THE 

### L IFE 

### L IMITS 

### S PECIFIED IN THE 

### D OCUMENT 

### I DENTIFIED IN 

### P ARAGRAPH 

### (g)(1)(ii)

OF 

### T HIS 

### 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


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

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.



### F IGURE 

### 1 TO 

### P ARAGRAPH 

### (i) OF 

### T HIS 

### AD—S PECIAL 

### C OMPLIANCE 

### T IMES

Designation Aircraft type applicability

Start date Compliance time (whichever occurs first after the ‘‘start date’’) A300 A310 A300–600

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 ye ars. 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.


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

F IGURE 

### 1 TO 

### P ARAGRAPH 

### (i) OF 

### T HIS 

### AD—S PECIAL 

### C OMPLIANCE 

### T IMES

### —Continued

Designation Aircraft type applicability

Start date Compliance time (whichever occurs first after the ‘‘start date’’) A300 A310 A300–600

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 ..... 13,2 00 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.


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

F IGURE 

### 1 TO 

### P ARAGRAPH 

### (i) OF 

### T HIS 

### AD—S PECIAL 

### C OMPLIANCE 

### T IMES

### —Continued

Designation Aircraft type applicability

Start date Compliance time (whichever occurs first after the ‘‘start date’’) A300 A310 A300–600

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 ..... 13,20 0 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

1 When 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.


## 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