10540 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules 

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. You 

may view this referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, Washington. 

For information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on February 

19, 2016. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–04292 Filed 2–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–3984; Directorate 

Identifier 2014–NM–119–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) 2013–10– 

03, for all Airbus Model A330–200, 

–200 Freighter, and –300 series 

airplanes; and Model A340–200, –300, 

–500, and –600 series airplanes. AD 

2013–10–03 currently requires one-time 

inspections for deformation and damage 

of the bogie beams of the main landing 

gear (MLG); repetitive inspections for 

damage and corrosion of the sliding 

piston sub-assembly on certain 

airplanes; and related investigative and 

corrective actions if necessary. Since we 

issued AD 2013–10–03, we have 

determined that certain one-time 

inspections are no longer necessary, 

certain compliance times may be 

extended, and an optional terminating 

action should be provided. This 

proposed AD would remove Model 

A340–500, and –600 series airplanes 

from the applicability, remove certain 

one-time inspections of the MLG bogie 

beams and the sliding piston subassembly; revise certain compliance 

times and provide, for certain airplanes, 

an optional terminating action for the 

repetitive actions. We are proposing this 

AD to detect and correct damage or 

corrosion under the bogie stop pad of 

both MLG bogie beams, which could 

result in a damaged bogie beam and 

consequent detachment of the beam 

from the airplane, or collapse of the 

MLG and departure of the airplane from 

the runway. 

DATES: We must receive comments on 

this proposed AD by April 15, 2016. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

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

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, 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 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–2016– 

3984; 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone: 425–227–1138; 

fax: 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2016–3984; Directorate Identifier 

2014–NM–119–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 May 13, 2013, we issued AD 

2013–10–03, Amendment 39–17456 (78 

FR 31386, May 24, 2013). AD 2013–10– 

03 requires actions intended to address 

an unsafe condition on all Airbus Model 

A330–200, –200 Freighter, and –300 

series airplanes; and Model A340–200, 

–300, –500, and –600 series airplanes. 

(AD 2013–10–03 superseded AD 2010– 

02–10, Amendment 39–16181 (75 FR 

4477, January 28, 2010)). 

Since we issued AD 2013–10–03, 

Amendment 39–17456 (78 FR 31386, 

May 24, 2013), we have determined that 

certain one-time inspections are no 

longer necessary, certain compliance 

times may be extended, and an optional 

terminating action should be provided. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2014– 

0120R1, dated August 31, 2015 (referred 

to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for all Airbus Model A330– 

200, –200 Freighter, and –300 series 

airplanes; and Model A340–200, –300, 

–500, and –600 series airplanes. The 

MCAI states: 

During a scheduled maintenance 

inspection on the Main Landing Gear (MLG), 

the bogie stop pad was found deformed and 

cracked. Upon removal of the bogie stop pad 

for replacement, the bogie beam was also 

found cracked. 

The results of a laboratory investigation 

indicated that an overload event had 

occurred and no fatigue propagation of the 

crack was evident. 

A second bogie beam crack was 

subsequently found on another aeroplane, 

located under a bogie stop pad which only 

had superficial paint damage. 

This condition, if not detected and 

corrected, could lead to landing gear bogie 

detachment from the aeroplane, or landing 

gear collapse, or a runway excursion, 


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possibly resulting in damage to the aeroplane 

and injury to the occupants. 

To address this potential unsafe condition, 

EASA issued * * * [an earlier AD] to require 

accomplishment of a one-time detailed 

inspection under the bogie stop pad of both 

MLG bogie beams. 

As a result of the one-time inspection 

required by that [earlier EASA] AD, 

applicable to A330, A340–200 and A340–300 

aeroplanes, numerous bogie stop pad were 

found corroded and a few cracked. 

The one-time inspection was retained in 

EASA AD 2011–0211 [http://

ad.easa.europa.eu/blob/easa_ad_2011_0211_

superseded.pdf/AD_2011-0211_1] [which 

corresponds to FAA AD 2013–10–03, 

Amendment 39–17456 (78 FR 31386, May 24, 

2013)], which superseded * * * [an earlier 

EASA AD], applicable to all A330 and A340 

aeroplanes, which also introduced repetitive 

inspections for A330, A340–200 and A340– 

300 aeroplanes, but not for the A340–500/- 

600 aeroplanes. 

Since issuance of EASA AD 2011–0211, 

further investigation accomplished by Airbus 

led to the conclusion that the one-time 

inspection in accordance with Airbus Service 

Bulletin (SB) A330–32–3220, or Airbus SB 

A340–32–4264, or Airbus SB A340–32–5087, 

as applicable, is no longer necessary and, for 

those aeroplanes, only the inspections (initial 

and repetitive) in accordance with Airbus SB 

A330–32–3248 or Airbus SB A340–32–4286, 

as applicable, must remain. 

In addition, Airbus also determined that 

repetitive inspections of the MLG in 

accordance with Airbus SB A340–32–5112 

are necessary for A340–500/-600 aeroplanes. 

Consequently, EASA issued * * * [another 

AD], which partially retained the 

requirements of EASA AD 2011–0211, which 

was superseded, and introduced repetitive 

detailed inspections of the MLG for A340– 

500 and A340–600 aeroplanes. 

Since that [EASA] AD was issued, it was 

determined that repetitive inspections of the 

MLG are not necessary on the A340–500/-600 

aeroplanes and that the threshold for the 

inspection of MLG P/N 10–210 series can be 

delayed. In addition, Airbus developed a 

mod of the MLG P/N 10–210 series that can 

be embodied both in production through 

mod 204421 and in service with Airbus SB 

A330–32–3268 or SB A340–32–4300, as 

applicable. This modification constitutes a 

terminating action for the repetitive 

inspections for aeroplanes equipped with 

MLG P/N 10–210 series. 

For the reasons described above, this 

[EASA] AD is revised and requires inspection 

of the MLG (with an amended threshold for 

MLG P/N 10–210 series) and introduces an 

option to terminate the repetitive inspection 

with a modification of the MLG P/N 10–210 

series. 

The required actions include 

repetitive detailed inspections for 

damage and corrosion of the sliding 

piston sub-assembly, and related 

investigative and corrective actions if 

necessary. Related investigative actions 

include a test for indications of 

corrosion and damage to the bogie 

assembly base material, and a magnetic 

particle inspection for cracks, corrosion, 

and damage of the bogie beam. 

Corrective actions include repairing 

affected parts. 

The optional terminating action 

modification of the bogie beam of an 

MLG having P/N 10–210 consists of 

installing a nickel under chrome 

coating, a new bogie beam stop pad, and 

new stop pad brackets. 

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–2016– 

3984. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A330–32–3248, Revision 02, dated April 

16, 2014. This service information 

describes procedures for doing a 

detailed inspection for damage and 

corrosion of the MLG sliding piston subassembly, bogie beam stop pad and the 

bogie beam under the stop pad; and 

related investigative and corrective 

actions. 

Airbus has also issued Service 

Bulletin A330–32–3268 and Airbus 

Service Bulletin A340–32–4300, both 

dated April 20, 2015. This service 

information describes procedures for 

modification of the bogie beam of an 

MLG having P/N 10–210, which 

includes installing a nickel under 

chrome coating, a new bogie beam stop 

pad, and new stop pad brackets. 

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. 

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 these same 

type designs. 

Explanation of ‘‘RC’’ Procedures and 

Tests in Service Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which procedures and tests 

in the service information are required 

for compliance with an AD. 

Differentiating these procedures and 

tests from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The procedures and tests 

identified as Required for Compliance 

(RC) in any service information have a 

direct effect on detecting, preventing, 

resolving, or eliminating an identified 

unsafe condition. 

As specified in a Note under the 

Accomplishment Instructions of the 

specified service information, 

procedures and tests that are identified 

as RC in any service information must 

be done to comply with the proposed 

AD. However, procedures and tests that 

are not identified as RC are 

recommended. Those procedures and 

tests that are not identified as RC may 

be deviated from using accepted 

methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of 

an alternative method of compliance 

(AMOC), provided the procedures and 

tests identified as RC can be done and 

the airplane can be put back in an 

airworthy condition. Any substitutions 

or changes to procedures or tests 

identified as RC will require approval of 

an AMOC. 

Costs of Compliance 

We estimate that this proposed AD 

affects 89 Model A330–200, –200 

Freighter, and –300 series airplanes of 

U.S. registry. 

We estimate that it would take about 

12 work-hours per product to comply 

with the basic requirements 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 

$90,780, or $1,020 per product. 

Currently, there are no affected Model 

A340–200, or –300, series airplanes on 

the U.S. Register. However, if an 

affected airplane is imported and placed 

on the U.S. Register in the future, it 

would be subject to the same perairplane cost specified above for the 

Model A330–200, –200 Freighter, and 

–300 series airplanes. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 24 work-hours, and 1 work-hour 

for reporting, and require parts costing 

$78, for a cost of $2,203 per product. We 

have no way of determining the number 

of aircraft that might need these actions. 

According to the manufacturer, all of 

the parts costs of the optional 


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terminating action specified in this 

proposed AD may be covered under 

warranty, thereby reducing the cost 

impact on affected individuals. We do 

not control warranty coverage for 

affected individuals. We have received 

no definitive data that would enable us 

to provide the work-hour cost estimates 

for the optional terminating action 

specified in this proposed AD. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

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) 

2013–10–03, Amendment 39–17456 (78 

FR 31386, May 24, 2013), and adding 

the following new AD: 

Airbus: Docket No. FAA–2016–3984; 

Directorate Identifier 2014–NM–119–AD. 

(a) Comments Due Date 

We must receive comments by April 15, 

2016. 

(b) Affected ADs 

This AD replaces AD 2013–10–03, 

Amendment 39–17456 (78 FR 31386, May 24, 

2013). 

(c) Applicability 

This AD applies to Airbus airplanes 

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

this AD, certificated in any category; all serial 

numbers, except those that have embodied 

Airbus Modification 204421 in production. 

(1) Model A330–201, –202, –203, –223, 

–223F, –243, –243F, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes. 

(2) Model A340–211, –212, –213, –311, 

–312, –313 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing gear. 

(e) Reason 

This AD was prompted by reports of 

corroded and cracked bogie beams under the 

bogie stop pad. We are issuing this AD to 

detect and correct damage or corrosion under 

the bogie stop pad of both main landing gear 

(MLG) bogie beams, which could result in a 

damaged bogie beam and consequent 

detachment of the beam from the airplane, or 

collapse of the MLG and departure of the 

airplane from the runway. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections, Related 

Investigative Actions, and Corrective 

Actions 

For Model A330–200, Model A330–200 

Freighter, and Model A330–300 series 

airplanes; and Model A340–200, and –300 

series airplanes; equipped with a MLG 

having part number (P/N) 201252 series, or 

P/N 201490 series, or P/N 10–210 series: Do 

the applicable actions required by paragraph 

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

(1) For airplanes equipped, as of the 

effective date of this AD, with a MLG that has 

been previously inspected as specified in 

Airbus Service Bulletin A330–32–3220, 

Airbus Service Bulletin A330–32–3248, 

Airbus Service Bulletin A340–32–4264, or 

Airbus Service Bulletin A340–32–4286, as 

applicable: At applicable times specified in 

paragraphs (h)(1) and (h)(2) of this AD, do a 

detailed inspection for damage (e.g., cracking 

and fretting) and corrosion of the MLG 

sliding piston subassembly, bogie beam stop 

pad, and the bogie beam under the stop pad; 

and do all applicable related investigative 

and corrective actions; in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3248, Revision 02, 

dated April 16, 2014; or Airbus Service 

Bulletin A340–32–4286, dated October 5, 

2011; as applicable, except as required by 

paragraph (j) of this AD. Do all applicable 

related investigative and corrective actions 

before further flight. Repeat the inspection of 

the MLG sliding piston sub-assembly, bogie 

beam stop pad, and the bogie beam under the 

stop pad, thereafter, at intervals not to exceed 

2,500 flight cycles or 24 months, whichever 

occurs first. 

(2) For airplanes equipped, as of the 

effective date of this AD, with a MLG that has 

not been previously inspected as specified in 

Airbus Service Bulletin A330–32–3220, 

Airbus Service Bulletin A330–32–3248, 

Airbus Service Bulletin A340–32–4264, or 

Airbus Service Bulletin, A340–32–4286, as 

applicable: At the applicable times specified 

in paragraphs (h)(3) and (h)(4) of this AD, do 

a detailed inspection for damage (e.g., 

cracking and fretting) and corrosion of the 

MLG sliding piston sub-assembly, bogie 

beam stop pad, and the bogie beam under the 

stop pad; and do all applicable related 

investigative and corrective actions; in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

32–3248, Revision 02, dated April 16, 2014; 

or Airbus Service Bulletin A340–32–4286, 

dated October 5, 2011; as applicable, except 


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as required by paragraph (j) of this AD. Do 

all applicable related investigative and 

corrective actions before further flight. 

Repeat the inspection of the MLG sliding 

piston sub-assembly, bogie beam stop pad, 

and the bogie beam under the stop pad, 

thereafter, at intervals not to exceed 2,500 

flight cycles or 24 months, whichever occurs 

first. 

(h) Compliance Times for Paragraph (g) of 

This AD Actions 

Do the applicable actions required by 

paragraph (g) of this AD at the applicable 

time specified in paragraph (h)(1), (h)(2), 

(h)(3), or (h)(4) of this AD. 

(1) For airplanes identified in paragraph 

(g)(1) of this AD having an MLG P/N 201252 

series and P/N 201490 series: Before the 

accumulation of 2,500 total flight cycles or 24 

months, whichever occurs first since the later 

of the times specified in paragraphs (h)(1)(i) 

and (h)(1)(ii) of this AD. 

(i) Since first flight after a MLG overhaul. 

(ii) Since first flight after the most recent 

accomplishment of an inspection of the MLG 

as specified in Airbus Service Bulletin A330– 

32–3220; Airbus Service Bulletin A330–32– 

3248; Airbus Service Bulletin A340–32–4286; 

or Airbus Service Bulletin A340–32–4264; as 

applicable. 

(2) For airplanes identified in paragraph 

(g)(1) of this AD having an MLG P/N 10–210 

series: Before the accumulation of 126 

months since first flight of the MLG on an 

airplane or since first flight on an airplane 

after the most recent inspection of the MLG 

as specified in Airbus Service Bulletin A330– 

32–3248, Revision 01, dated December 13, 

2012; or Airbus Service Bulletin A330–32– 

3248, Revision 02, dated April 16, 2014; or 

Airbus Service Bulletin A340–32–4286, 

dated October 5, 2011; as applicable. 

(3) For airplanes identified in paragraph 

(g)(2) of this AD having an MLG P/N 201252 

series and P/N 201490 series: At the later of 

the times specified in paragraphs (h)(3)(i) and 

(h)(3)(ii) of this AD. 

(i) Before the accumulation of 2,500 total 

flight cycles or 24 months, whichever occurs 

first since the later of the times specified in 

paragraphs (h)(3)(i)(A) and (h)(3)(i)(B) of this 

AD. 

(A) Since first flight of the MLG on an 

airplane. 

(B) Since first flight after a MLG overhaul. 

(ii) Within 16 months after the effective 

date of this AD. 

(4) For airplanes identified in paragraph 

(g)(2) of this AD having MLG P/N 10–210 

series: Before the accumulation of 126 

months since first flight of the MLG on an 

airplane. 

(i) Optional Overhaul 

For the purposes of this AD, 

accomplishment of an MLG overhaul is 

acceptable instead of an inspection required 

by paragraph (g) of this AD. The inspections 

required by paragraph (g) of this AD are not 

terminated by an MLG overhaul, but are 

required at the next applicable compliance 

time required by paragraph (g) of this AD. 

(j) Service Information Exception 

If the applicable service information 

specified in paragraph (g) of this AD specifies 

to contact Messier-Dowty for instructions, or 

if any repair required by paragraph (g) of this 

AD is beyond the maximum repair allowance 

specified in the applicable service 

information specified in paragraph (g) of this 

AD: Before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA). 

(k) Reporting Requirement 

After accomplishing any of the corrective 

actions required by paragraph (g) of this AD 

or any repair required by paragraph (j) of this 

AD: Report the results of the corrective 

actions or repair to Airbus, Customer 

Services Directorate, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex France; Attn: 

SDC32 Technical Data and Documentation 

Services; fax: +33 5 61 93 28 06; email: 

sb.reporting@airbus.com, at the applicable 

time specified in paragraph (k)(1) or (k)(2) of 

this AD. 

(1) If the corrective action or repair was 

done on or after the effective date of this AD: 

Submit the report within 90 days after doing 

corrective action or repair. 

(2) If the corrective action or repair was 

done prior to the effective date of this AD: 

Submit the report within 90 days after the 

effective date of this AD. 

(l) Terminating Action Limitation 

Accomplishment of corrective actions as 

required by paragraph (g) of this AD does not 

constitute terminating action for the 

repetitive inspections required by this AD. 

(m) Optional Terminating Action for Certain 

Airplanes 

For airplanes with any MLG having P/N 

10–210 series: Modification on an airplane of 

the bogie beam of each MLG having P/N 10– 

210 series as specified in the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3268, dated April 

20, 2015; or Airbus Service Bulletin A340– 

32–4300, dated April 20, 2015; as applicable; 

constitutes terminating action for the 

requirements of this AD for that airplane, 

provided that, following in-service 

modification, the airplane remains in postservice bulletin configuration. 

(n) Credit for Previous Actions 

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 service 

information identified in paragraph (n)(1), 

(n)(2), or (n)(3), (n)(4), or (n)(5) of this AD. 

(1) Airbus Service Bulletin A330–32–3248, 

dated October 5, 2011, which is not 

incorporated by reference in this AD. 

(2) Airbus Service Bulletin A330–32–3248, 

Revision 01, including Appendix 01, dated 

December 13, 2012, which was incorporated 

by reference in AD 2013–10–03, Amendment 

39–17456 (78 FR 31386, May 24, 2013). 

(3) Airbus Service Bulletin A330–32–3220, 

dated October 10, 2008, which was 

incorporated by reference in AD 2010–02–10, 

Amendment 39–16181 (75 FR 4477, January 

28, 2010). 

(4) Airbus Service Bulletin A330–32–3220, 

Revision 01, dated October 5, 2011, which 

was incorporated by reference in AD 2013– 

10–03, Amendment 39–17456 (78 FR 31386, 

May 24, 2013). 

(5) Airbus Service Bulletin A330–32–3220, 

Revision 02, dated December 13, 2012, which 

was incorporated by reference in AD 2013– 

10–03, Amendment 39–17456 (78 FR 31386, 

May 24, 2013). 

(o) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–227–1138; fax: 425–227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

(i) 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. 

(ii) AMOCs approved previously for AD 

2013–10–03, Amendment 39–17456 (78 FR 

31386, May 24, 2013), are not approved as 

AMOCs with 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 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (j) of this AD: If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(4) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
10544 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(p) Special Flight Permits 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed if any crack is 

found during any inspection required by this 

AD. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2014–0120R1, dated August 31, 2015, for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2016–3984. 

(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 February 

19, 2016. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–04290 Filed 2–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–2859; Directorate 

Identifier 2016–NE–04–AD] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Turbomeca S.A. Arriel 1D and 1D1 

turboshaft engines with a premodification (mod) TU357 gas generator 

module (M03), installed. This proposed 

AD was prompted by reports of 

divergent rubbing between the piston 

shaft small diameter labyrinth and the 

rear bearing support. This proposed AD 

would require removing the premodification (mod) TU357 gas generator 

module (M03) and replacing with a part 

eligible for installation. We are 

proposing this AD to prevent failure of 

the labyrinth seal and engine, in-flight 

shutdown, and loss of control of the 

helicopter. 

DATES: We must receive comments on 

this proposed AD by May 2, 2016. 

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. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: 202–493–2251. 

For service information identified in 

this NPRM, contact Turbomeca S.A., 

40220 Tarnos, France; phone: 33 (0)5 59 

74 40 00; fax: 33 (0)5 59 74 45 15. You 

may view this service information at the 

FAA, Engine & Propeller Directorate, 

1200 District Avenue, Burlington, MA. 

For information on the availability of 

this material at the FAA, call 781–238– 

7125. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

2859; 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 

mandatory continuing airworthiness 

information (MCAI), the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

in the ADDRESSES section. Comments 

will be available in the AD docket 

shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Philip Haberlen, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7770; fax: 781–238–7199; 

email: philip.haberlen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this NPRM. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2016–2859; Directorate Identifier 2016– 

NE–04–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this NPRM. We will consider 

all comments received by the closing 

date and may amend this NPRM 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 with FAA 

personnel concerning this NPRM. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2016– 

0009, dated January 13, 2016 (referred to 

hereinafter as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Some cases of divergent rubbing between 

the piston shaft small diameter labyrinth and 

the rear bearing support have been reported. 

This condition, if not corrected, could lead 

to an uncommanded engine in-flight 

shutdown. 

You may obtain further information 

by examining the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

2859. 

Related Service Information 

Turbomeca S.A. has issued 

Mandatory Service Bulletin (MSB) No. 

292 72 1357, Version B, dated 

November 12, 2015. The MSB describes 

procedures for installing a postmodification (mod) TU357 gas generator 

module (M03). 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 France, and is 

approved for operation in the United 

States. Pursuant to our bilateral 


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