40942 Federal Register / Vol. 80, No. 134 / Tuesday, July 14, 2015 / Proposed Rules 

Issued in Washington, DC, on June 30, 

2015. 

Kathleen B. Hogan, 

Deputy Assistant Secretary for Energy 

Efficiency and Renewable Energy. 

[FR Doc. 2015–17252 Filed 7–13–15; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2461; Directorate 

Identifier 2013–NM–202–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

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 

currently requires 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. 

Since we issued AD 2009–18–15, we 

have determined that existing 

maintenance requirements and 

airworthiness limitations are inadequate 

to ensure the structural integrity of the 

airplane. This proposed AD would 

require revising the maintenance or 

inspection program to incorporate new 

maintenance requirements and 

airworthiness limitations. We are 

proposing this AD to prevent failure of 

certain system components, which 

could result in reduced structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by August 28, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this proposed 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

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 proposed 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. Comments will 

be available in the AD docket shortly 

after receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–2461; Directorate Identifier 

2013–NM–202–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On August 24, 2009, we issued AD 

2009–18–15, Amendment 39–16011 (74 

FR 48143, September 22, 2009). AD 

2009–18–15 requires actions intended to 

address an unsafe condition 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). 

Since we issued AD 2009–18–15, 

Amendment 39–16011 (74 FR 48143, 

September 22, 2009), we have 

determined that more restrictive 

maintenance requirements and 

airworthiness limitations are necessary. 

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 by searching for 

and locating Docket No. FAA–2015– 

2461. 


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Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information, which describes 

procedures for revising the maintenance 

or inspection program to incorporate 

new maintenance requirements and 

airworthiness limitations. 

• For Model A300 series airplanes: 

‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Subpart 1–3: Demonstrated fatigue lives’’ of 

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): ‘‘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 Model A300–600 

Airworthiness Limitations Section. 

• For Model A310 series airplanes: 

‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Subpart 1–3: Demonstrated fatigue lives’’ of 

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 NPRM. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

affects 177 airplanes of U.S. registry. 

The 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 would take 

about 1 work-hour per product to 

comply with the new ALS revision of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed 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. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive AD 

2009–18–15, Amendment 39–16011 

(74 FR 48143, September 22, 2009), and 

adding the following new AD: 

Airbus: Docket No. FAA–2015–2461; 

Directorate Identifier 2013–NM–202–AD. 

(a) Comments Due Date 

We must receive comments by August 28, 

2015. 

(b) Affected ADs 

This AD replaces AD 2009–18–15, 

Amendment 39–16011 (74 FR 48143, 

September 22, 2009). 

(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 


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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. 

(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 

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, with or without using 

the information in Airbus Service 

Information Letter 32–118, Revision 02, 

dated October 24, 2007: 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 after the ‘‘start 

date’’) A300 A310 A300– 

600 P/N 

Landings Calendar time X X X 

MAIN LANDING GEAR 

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. 

Aft pintle pin ............. 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. 

A32140036200xx X December 13, 2007 13,500 ..................... 9 years. 

A32140036202xx X December 13, 2007 13,500 ..................... 9 years. 

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

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

Half ball housing 

(Fwd pintle bearing).

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. 


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

Pin (Multiple link/

Frame 50).

A53833451200xx X December 13, 2007 13,500 ..................... 9 years.. 

A53833451206xx X December 13, 2007 13,500 ..................... 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 X December 13, 2007 N/A .......................... 30 months. 

SL40089 X December 13, 2007 N/A .......................... 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 X December 13, 2007 N/A .......................... 30 months. 

SL40114P X X April 25, 2007 ........ N/A .......................... 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 X December 13, 2007 13,500 ..................... 9 years. 

C65815–1 X December 13, 2007 13,500 ..................... 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 X December 13, 2007 N/A .......................... 30 months. 

SL40089 X December 13, 2007 N/A .......................... 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. 

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

D55955 X X X April 25, 2007 ........ 13,500 ..................... 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 X December 13, 2007 13,200 ..................... 9 years. 

C62231–2 X December 13, 2007 13,200 ..................... 9 years. 


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

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

C62223–20 X X X April 25, 2007 ........ 13,500 ..................... 9 years. 

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 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 134 / Tuesday, July 14, 2015 / Proposed Rules 40947 

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. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. You may 

view this service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on June 25, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–17201 Filed 7–13–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2714; Directorate 

Identifier 2014–SW–052–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for Airbus 

Helicopters Model AS332C1, AS332L1, 

AS332L2, EC225LP, AS–365N2, AS 365 

N3, EC 155B, and EC155B1 helicopters 

with an energy absorbing seat (seat). 

This proposed AD would require 

inspecting for the presence of labels that 

prohibit stowing anything under the 

seat. If a label is missing or not clearly 

visible to each occupant, installing a 

label would be required. This proposed 

AD is prompted by the discovery that 

required labels had not been 

systematically installed. The proposed 

actions are intended to prevent objects 

from being stowed under the seat as 

these objects could reduce the energyabsorbing function of the seat, resulting 

in injury to the seat occupants during an 

accident. 

DATES: We must receive comments on 

this proposed AD by September 14, 

2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

European Aviation Safety Agency 

(EASA) AD, the economic evaluation, 

and other information. The street 

address for the Docket Operations Office 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

For service information identified in 

this proposed AD, contact Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax 

(972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS