This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

14642 

Vol. 82, No. 54 

Wednesday, March 22, 2017 

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: Supplemental notice of 

proposed rulemaking (SNPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposal 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. This action revises the 

notice of proposed rulemaking (NPRM) 

by adding a replacement of certain main 

landing gear (MLG) with MLG that have 

an improved bogie beam. We are 

proposing this AD to address the unsafe 

condition on these products. Since these 

actions impose an additional burden 

over those proposed in the NPRM, we 

are reopening the comment period to 

allow the public the chance to comment 

on these proposed changes. 

DATES: We must receive comments on 

this SNPRM by May 8, 2017. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

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

p.m., Monday through Friday, except 

Federal holidays. 

For Airbus service information 

identified in this SNPRM, contact 

Airbus SAS, Airworthiness Office— 

EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; 

telephone: +33 5 61 93 36 96; fax: +33 

5 61 93 45 80; email: 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

For Messier-Bugatti-Dowty service 

information identified in this SNPRM, 

contact Messier Services Americas, 

Customer Support Center, 45360 Severn 

Way, Sterling, VA 20166–8910; phone: 

703–450–8233; fax: 703–404–1621; 

Internet: https://techpubs.services/ 

messier-dowty.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 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’’). 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)). 

We issued an NPRM to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Airbus Model A330–200, 

–200 Freighter, and –300 series 

airplanes; and Model A340–200 and 

–300 series airplanes. The NPRM 

published in the Federal Register on 

March 1, 2016 (81 FR 10540) (‘‘the 

NPRM’’). The NPRM was prompted by 

reports of corroded and cracked bogie 

beams under the bogie stop pad. The 

NPRM proposed to 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. 

Actions Since the NPRM Was Issued 

Since we issued the NPRM, we have 

determined that MLG having part 

number (P/N) 201252 series and P/N 

201490 series should be replaced with 

a MLG that has an improved bogie 

beam, which would constitute 

terminating action for the repetitive 

inspections on the modified MLG. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2016–0108, 

dated June 8, 2016 (referred to after this 


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as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A330–200, 

–200 Freighter, and –300 series 

airplanes; and Model A340–200 and 

–300 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, 

possibly resulting in damage to the aeroplane 

and injury to the occupants and/or people on 

the ground. 

To address this potential unsafe condition, 

EASA issued AD 2008–0223 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 [EASA] AD, 

numerous bogie stop pad were found 

corroded and a few cracked. The one-time 

inspection was retained in EASA AD 2011– 

0211 [which corresponds to FAA AD 2013– 

10–03], which superseded EASA AD 2008– 

0223, which also introduced repetitive 

inspections, except for A340–500/–600 

aeroplanes. 

After EASA AD 2011–0211 was issued, 

further investigation led to the conclusion 

that the one-time inspection was no longer 

necessary and only the repetitive inspections 

should remain. In addition, it was 

determined that repetitive inspections were 

also necessary for MLG on A340–500/–600 

aeroplanes. 

Prompted by these conclusions, EASA 

issued AD 2014–0120, partially retaining the 

requirements of EASA AD 2011–0211, which 

was superseded, and introducing repetitive 

detailed inspections of the MLG on A340– 

500 and A340–600 aeroplanes. Subsequently, 

further analysis indicated that repetitive 

inspections of the MLG on A340–500/–600 

aeroplanes were not necessary after all. In 

addition, the threshold for the inspection of 

MLG P/N 10–210 series was raised from 24 

to 126 months, and Airbus developed a 

modification of the MLG P/N 10–210 series 

which provides an (optional) terminating 

action for the repetitive inspections. 

Consequently, EASA AD 2014–0120 was 

revised to delete the requirements for A340– 

500/–600 aeroplanes, to amend the 

inspection threshold for MLG P/N 10–210 

series, and to introduce an optional 

terminating action for aeroplanes with MLG 

P/N 10–210 series. 

Since EASA AD 2014–0120R1 was issued, 

Airbus developed a modification (mod 

205289) of the MLG P/N 201252 series and 

P/N 201490 series that must be embodied in 

service with Airbus SB A330–32–3275 or SB 

A340–32–4305. It was also identified that 

A340–500/–600 aeroplanes could be removed 

from the applicability of this [EASA] AD as 

no more actions were required on these 

aeroplanes. 

For the reason described above, this 

[EASA] AD retains the requirements of EASA 

AD 2014–0120R1, which is superseded, 

removes the A340–500/–600 aeroplanes from 

the Applicability and requires the 

modification of the MLG P/N 201252 series 

and P/N 201490 series, which constitutes 

terminating action for the repetitive 

inspections required by this [EASA] AD. 

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 required terminating action (for 

MLG having P/N 201252 series or P/N 

201490 series) and the optional 

terminating action (for MLG having P/N 

10–210) are modifications of the bogie 

beam of an MLG, which consist 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 the following 

service information. 

• Airbus Service Bulletin A330–32– 

3248, Revision 05, including Appendix 

1, dated May 4, 2016; and Airbus 

Service Bulletin A340–32–4286, 

Revision 02, including Appendix 1, 

dated January 5, 2016; which describe 

procedures for doing an inspection for 

damage and corrosion of the MLG 

sliding piston sub-assembly, bogie beam 

stop pad and the bogie beam under the 

stop pad, and related investigative and 

corrective actions. These documents are 

distinct since they apply to different 

airplane models. 

• Airbus Service Bulletin A330–32– 

3268, Revision 01, dated September 21, 

2015, which describes procedures for 

modification of the bogie beam of an 

MLG having P/N 10–210 that includes 

installing a nickel under chrome 

coating, a new bogie beam stop pad, and 

new stop pad brackets. 

• Airbus Service Bulletin A330–32– 

3275, dated December 23, 2015, which 

describes procedures for modification of 

the bogie beam of an MLG having P/N 

201252 series or P/N 201490 series that 

include installing a nickel under 

chrome coating, a new bogie beam stop 

pad, and new stop pad brackets. 

• Airbus Service Bulletin A340–32– 

4300, dated April 20, 2015; and 

Revision 01, dated September 21, 2015; 

which describe procedures for 

modification of the bogie beam of an 

MLG having P/N 10–210 that include 

installing a nickel under chrome 

coating, a new bogie beam stop pad, and 

new stop pad brackets. These service 

bulletins are distinct since they are 

different revision levels. 

• Airbus Service Bulletin A340–32– 

4305, dated December 23, 2015, which 

describes procedures for modification of 

the bogie beam of an MLG having P/N 

201252 series or P/N 201490 series that 

includes installing a nickel under 

chrome coating, a new bogie beam stop 

pad, and new stop pad brackets. 

Messier-Bugatti-Dowty has issued the 

following service information. 

• Messier-Bugatti-Dowty Service 

Bulletin A33/34–32–305, including 

Appendix A, dated April 13, 2015, 

which describes procedures for 

modification of the bogie beam of an 

MLG having MLG P/N 10–210 series 

that includes installing a nickel under 

chrome coating, a new bogie beam stop 

pad, and new stop pad brackets. 

• Messier-Bugatti-Dowty Service 

Bulletin A33/34–32–306, Revision 1, 

including Appendix A, dated May 31, 

2016, which describes procedures for 

modification of the bogie beam of an 

MLG having P/N 201252 series or P/N 

201490 series that 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. 

Comments 

We gave the public the opportunity to 

participate in developing this proposed 

AD. We considered the comments 

received on the proposal and the FAA’s 

response to each comment. 

Requests To Revise Applicability and 

Terminating Action 

Air France (AF) and American 

Airlines (AAL) requested that we revise 

the applicability of the proposed AD to 

exclude airplanes that have had Airbus 

Modification 204421 or Airbus 


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Modification 205289 incorporated in 

production. 

AAL also requested that we exclude 

airplanes from the applicability that 

have accomplished the actions specified 

in Airbus Service Bulletin A330–32– 

3268, dated April 20, 2015, which 

describes procedures for modification of 

the bogie beam of an MLG having P/N 

10–210, and Airbus Service Bulletin 

A330–32–3275, dated December 23, 

2015, which describes procedures for 

modification of the bogie beam of an 

MLG having P/N 201490. 

AAL and AF also requested that we 

add Airbus Service Bulletin A330–32– 

3275, dated December 23, 2015, as a 

terminating action in paragraph (m) of 

the proposed AD. AF also asked that we 

add Airbus Service Bulletin A340–32– 

4305, dated December 23, 2015, as a 

terminating action in paragraph (m) of 

the proposed AD. AF and AAL 

referenced the applicability in the MCAI 

as justification for the requests. 

We partially agree with the 

commenters’ requests. We have revised 

paragraph (c) of this proposed AD to 

exclude airplanes that have embodied 

Airbus Modification 204421 or Airbus 

Modification 205289 in production, 

which corresponds with the MCAI. 

However, we have not revised 

paragraph (c) of this proposed AD to 

exclude airplanes on which Airbus 

Service Bulletin A330–32–3268, dated 

April 20, 2015; or Airbus Service 

Bulletin A330–32–3275, dated 

December 23, 2015; has been done 

because those airplanes are not 

excluded from the MCAI. 

We have added information to 

paragraph (m) of this proposed AD to 

specify that accomplishing the actions 

specified in Messier-Bugatti-DowtyService Bulletin A33/34–32–305, 

including Appendix A, dated April 13, 

2015, for MLG having P/N 10–210, 

constitutes terminating action for the 

repetitive inspections. We also have 

added information in paragraph (m) of 

this proposed AD to specify that 

accomplishing the actions specified in 

the service information referenced in 

paragraph (k) of this proposed AD 

(which includes references to Airbus 

Service Bulletin A330–32–3275, dated 

December 23, 2015; and Airbus Service 

Bulletin A340–32–4305, dated 

December 23, 2015) constitutes 

terminating action for the repetitive 

inspections. 

Additional Changes to This SNPRM 

We have clarified the affected 

airplanes for paragraphs (h)(1) and (h)(3) 

of this AD by changing the text ‘‘For 

airplanes . . . having an MLG P/N 

201252 series and P/N 201490 series’’ to 

‘‘For airplanes . . . having an MLG P/ 

N 201252 series or P/N 201490 series’’ 

(replaced the ‘‘and’’ with an ‘‘or’’). 

We have removed the reporting 

requirements from this SNPRM. We 

have also revised the Costs of 

Compliance section of this SNPRM to 

reflect the revised proposed 

requirements. 

FAA’s Determination and Requirements 

of This SNPRM 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

Certain changes described above 

expand the scope of the NPRM. As a 

result, we have determined that it is 

necessary to reopen the comment period 

to provide additional opportunity for 

the public to comment on this SNPRM. 

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 

13 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 

$98,345, or $1,105 per product. 

Currently, there are no 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 per-airplane 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 require parts 

costing $78, for a cost of $2,118 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 

terminating action specified in this 

SNPRM may be covered under 

warranty, thereby reducing the cost 

impact on affected individuals. We do 

not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 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. 

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: 


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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 May 8, 

2017. 

(b) Affected ADs 

This AD replaces AD 2013–10–03, 

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

2013) (‘‘AD 2013–10–03’’). 

(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 airplanes that have 

embodied Airbus Modification 204421 or 

Airbus Modification 205289 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, and –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; this condition could 

result in a damaged bogie beam and 

consequent detachment of the beam from the 

airplane, collapse of the MLG, or departure 

of the airplane from the runway, possibly 

resulting in damage to the airplane and 

injury to occupants. 

(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, –200 Freighter, and 

–300 series airplanes; and Model A340–200 

and –300 series airplanes; equipped with a 

MLG having part number (P/N) 201252 

series, 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 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 05, 

including Appendix 1, dated May 4, 2016; or 

Airbus Service Bulletin A340–32–4286, 

Revision 02, including Appendix 1, dated 

January 5, 2016; 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 05, including Appendix 1, 

dated May 4, 2016 or Airbus Service Bulletin 

A340–32–4286, Revision 02, including 

Appendix 1, dated January 5, 2016; 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. 

(h) Compliance Times for the Actions 

Required by Paragraph (g) of This AD 

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 or 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, or Airbus Service Bulletin A340– 

32–4286, as applicable. 

(3) For airplanes identified in paragraph 

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

series or 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) MLG Modification 

For airplanes equipped with MLG having 

P/N 201252 series or MLG having P/N 

201490 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 overhaul as of the 

effective date of this AD, as applicable, 

replace that MLG with a MLG having P/N 

201252 series or MLG having P/N 201490 

series that has an improved bogie beam, as 

defined in Airbus Service Bulletin A330–32– 

3275, dated December 23, 2015; or Airbus 

Service Bulletin A340–32–4305, dated 

December 23, 2015; as applicable; and in 

accordance with the Accomplishment 

Instructions of Messier-Bugatti-Dowty 

Service Bulletin A33/34–32–306, Revision 1, 

including Appendix A, dated May 31, 2016. 


jstallworth on DSK7TPTVN1PROD with PROPOSALS
14646 Federal Register / Vol. 82, No. 54 / Wednesday, March 22, 2017 / Proposed Rules 

(l) Terminating Action Limitation 

Accomplishment of corrective actions 

required by paragraph (g) of this AD does not 

constitute terminating action for the 

repetitive inspections required by this AD. 

(m) Terminating Action for Certain 

Airplanes 

(1) For airplanes with any MLG having P/ 

N 10–210 series: Modification of the bogie 

beam of each MLG having P/N 10–210 series, 

as specified in Airbus Service Bulletin A330– 

32–3268, Revision 01, dated September 21, 

2015; or Airbus Service Bulletin A340–32– 

4300, dated April 20, 2015; or Revision 01, 

dated September 21, 2015; as applicable; and 

in accordance with the Accomplishment 

Instructions of Messier-Bugatti-Dowty 

Service Bulletin A33/34–32–305, including 

Appendix A, dated April 13, 2015; 

constitutes terminating action for the 

repetitive inspection requirements of this AD 

for that airplane, provided that, following inservice modification, the airplane remains in 

post-service bulletin configuration. 

(2) For airplanes with any MLG having P/ 

N 201252 series or P/N 201490 series: 

Installation of both left-hand and right-hand 

MLG having P/N 201252 series or P/N 

201490 series that has an improved bogie 

beam, as required by paragraph (k) of this 

AD, constitutes terminating action for the 

repetitive inspections requirements of this 

AD for that airplane, provided that, following 

in-service modification, the airplane remains 

in post-service bulletin configuration. 

(n) Parts Installation Prohibition 

Do not install on any airplane a pre-Airbus 

modification MLG having P/N 201252 series 

or pre-Airbus modification MLG having P/N 

201490 series, as specified in paragraph 

(n)(1) or (n)(2) of this AD, as applicable; or 

a pre-Airbus modification MLG having P/N 

10–210 series, as specified in paragraph 

(n)(3) or (n)(4) of this AD, as applicable. 

(1) For any airplane that is in post-Airbus 

Modification 205289 configuration, or on 

which the modification required by 

paragraph (k) of this AD has been done: From 

the effective date of this AD. 

(2) For any airplane that is in pre-Airbus 

Modification 205289 configuration, or on 

which the modification required by 

paragraph (k) of this AD has not been done: 

After modification of that airplane, as 

required by paragraph (k) of this AD. 

(3) For any airplane that is in post-Airbus 

Modification 204421 configuration, or on 

which the modification specified in 

paragraph (m)(1) of this AD has been done: 

From the effective date of this AD. 

(4) For an airplane that is in pre-Airbus 

Modification 204421, or on which the 

modification required by paragraph (m)(1) of 

this AD has not been done: After 

modification of that airplane, as required by 

paragraph (m)(1) of this AD. 

(o) 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 service 

information identified in paragraphs (o)(1)(i) 

through (o)(1)(vii) or (o)(2) of this AD, as 

applicable. 

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

dated October 5, 2011, which is not 

incorporated by reference in this AD. 

(ii) 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). 

(iii) Airbus Service Bulletin A330–32– 

3248, Revision 02, dated April 16, 2014, 

which is not incorporated by reference in this 

AD. 

(iv) Airbus Service Bulletin A330–32– 

3248, Revision 03, dated November 27, 2015, 

which is not incorporated by reference in this 

AD. 

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

Revision 04, dated January 5, 2016, which is 

not incorporated by reference in this AD. 

(vi) Airbus Service Bulletin A340–32– 

4286, dated October 5, 2011, which was 

incorporated by reference in AD 2013–10–03, 

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

2013). 

(vii) Airbus Service Bulletin A340–32– 

4286, Revision 01, dated November 27, 2015, 

which is not incorporated by reference in this 

AD. 

(2) This paragraph provides credit for the 

actions required by paragraph (k) of this AD, 

if those actions were performed before the 

effective date of this AD using MessierBugatti-Dowty Service Bulletin A33/34–32– 

306, dated December 21, 2015, which is not 

incorporated by reference in this AD. 

(p) 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 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. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2016–0108, dated June 8, 2016, for related 

information. This MCAI may be found in the 

AD docket on the Internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2016–3984. 

(2) For Airbus service information 

identified in this AD, contact Airbus SAS, 

Airworthiness Office—EAL, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone: +33 5 61 93 36 96; fax: 

+33 5 61 93 45 80; email: 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. For MessierBugatti-Dowty service information identified 

in this AD, contact Messier Services 

Americas, Customer Support Center, 45360 

Severn Way, Sterling, VA 20166–8910; 

phone: 703–450–8233; fax: 703–404–1621; 

Internet: https://techpubs.services/messierdowty.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 March 9, 

2017. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2017–05251 Filed 3–21–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9380; Directorate 

Identifier 2016–NE–21–AD 

RIN 2120–AA64 

Airworthiness Directives; CFE 

Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Proposed rule; withdrawal. 

SUMMARY: The FAA is withdrawing a 

notice of proposed rulemaking (NPRM). 

The NPRM proposed a new 


jstallworth on DSK7TPTVN1PROD with PROPOSALS