66518 Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations 

Instructions of Bombardier Service Bulletin 

84–30–10, Revision E, dated October 10, 

2014, within the compliance times specified 

in paragraph (g) of this AD. 

(2) Bombardier Service Bulletin 84–30–10, 

Revision A, dated April 7, 2008. 

(3) Bombardier Service Bulletin 84–30–10, 

Revision B, dated January 20, 2010. 

(4) Bombardier Service Bulletin 84–30–10, 

Revision C, dated July 14, 2011. 

(5) Bombardier Service Bulletin 84–30–10, 

Revision D, dated December 20, 2011. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO, 

ANE–170, 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 ACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

516–228–7300; fax 516–794–5531. 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. 

(2) Contacting the Manufacturer: 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, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

TCCA; or Bombardier, Inc.’s TCCA DAO. If 

approved by the DAO, the approval must 

include the DAO-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2015–24, dated 

August 24, 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–2016–6148. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Bombardier Service Bulletin 84–30–10, 

Revision E, dated October 10, 2014. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone: 416–375–4000; fax: 416–375– 

4539; email: thd.qseries@

aero.bombardier.com; Internet: http://

www.bombardier.com. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 12, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–22705 Filed 9–27–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0828; Directorate 

Identifier 2012–NM–036–AD; Amendment 

39–18637; AD 2016–18–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2009–15– 

17 for certain Airbus Model A330–200 

and –300 series airplanes; and Model 

A340–200 and –300 series airplanes. AD 

2009–15–17 required an inspection for 

damage to the protective treatments or 

any corrosion of all main landing gear 

(MLG) bogie beams, and application of 

protective treatments if no damage or 

corrosion was found. If any damage or 

corrosion was found, corrective action 

followed by the application of 

protective treatments was required. This 

new AD continues to require 

inspections for damage to the protective 

treatments or any corrosion of all MLG 

bogie beams, application of protective 

treatments, and corrective action if 

necessary. This new AD also requires 

modification of the MLG bogie beams, 

which terminates the repetitive 

inspections for any modified bogie 

beam. This new AD allows optional 

methods of compliance for certain 

actions, and adds Airbus Model A330– 

200 Freighter series airplanes to the 

applicability. This new AD revises the 

compliance times and adds a one-time 

inspection for airplanes that were 

inspected too early. This AD was 

prompted by reports of thin paint coats 

and paint degradation on enhanced 

main landing gear (MLG) bogie beams, 

as well as reports that some airplanes 

have been inspected too early and not 

re-inspected as needed. We are issuing 

this AD to detect and correct damage or 

corrosion of the MLG bogie beams, 

which could cause a runway excursion 

event, bogie beam detachment from the 

airplane, or MLG collapse, and could 

result in damage to the airplane and 

injury to the occupants. 

DATES: This AD is effective November 2, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 2, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of September 2, 2009 (74 FR 

37523, July 29, 2009). 

ADDRESSES: For Airbus service 

information identified in this final rule, 

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-Dowty service information 

identified in this final rule, contact 

Messier-Dowty: Messier Services 

Americas, Customer Support Center, 

45360 Severn Way, Sterling, VA 20166– 

8910; telephone: 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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2013– 

0828. 

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–2013– 

0828; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone: 800–647– 


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5527) is Docket Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC 20590. 

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: 

Discussion 

We issued a second supplemental 

notice of proposed rulemaking (SNPRM) 

to amend 14 CFR part 39 to supersede 

AD 2009–15–17, Amendment 39–15980 

(74 FR 37523, July 29, 2009) (‘‘AD 2009– 

15–17’’). AD 2009–15–17 applied to 

certain Airbus Model A330–200 and 

–300 series airplanes, and Model A340– 

200 and –300 series airplanes. The 

second SNPRM published in the 

Federal Register on February 5, 2016 

(81 FR 6185) (‘‘the second SNPRM’’). 

We preceded the second SNPRM with 

the first SNPRM, which was published 

in the Federal Register on March 5, 

2014 (79 FR 12414) (‘‘the first SNPRM’’). 

We preceded the first SNPRM with a 

notice of proposed rulemaking (NPRM) 

that published in the Federal Register 

on September 25, 2013 (78 FR 58978) 

(‘‘the NPRM’’). The NPRM was 

prompted by reports of thin paint coats 

and paint degradation on enhanced 

MLG bogie beams. The NPRM proposed 

to continue to require inspections for 

damage to the protective treatments or 

any corrosion of all MLG bogie beams, 

application of protective treatments, and 

corrective action if necessary. The 

NPRM also proposed to require 

modification of the MLG bogie beams, 

which would terminate the repetitive 

inspections for any modified bogie 

beam. In addition, the NPRM proposed 

to allow optional methods of 

compliance for certain actions, and to 

add Airbus Model A330–200 Freighter 

series airplanes to the applicability. The 

first SNPRM proposed to revise the 

compliance times and add a one-time 

inspection for airplanes that were 

inspected too early. The second SNPRM 

proposed to clarify the required actions 

and the specific configurations to which 

the actions must be applied. We are 

issuing this AD to detect and correct 

damage or corrosion of the MLG bogie 

beams, which could cause a runway 

excursion event, bogie beam detachment 

from the airplane, or MLG collapse, and 

could result in damage to the airplane 

and injury to the occupants. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2013– 

0267R1, dated March 4, 2014; corrected 

May 8, 2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Airbus 

Model A330–200 Freighter, –200, and 

–300 series airplanes; and Model A340– 

200 and –300 series airplanes. The 

MCAI states: 

The operator of an A330 aeroplane (which 

has a common bogie beam with the A340) 

reported a fracture of the Right Hand (RH) 

main landing gear (MLG) bogie beam, which 

occurred while turning during low speed taxi 

maneuvers. The bogie fractured aft of the 

pivot point and remained attached to the 

sliding tube by the brake torque reaction 

rods. After this RH bogie failure, the 

aeroplane continued for approximately 40 

meters on the forks of the sliding member 

before coming to rest on the taxiway. 

The investigations revealed that this event 

was due to corrosion pitting occurring on the 

bore of the bogie beam. 

This condition, if not detected and 

corrected, could lead to a runway excursion 

event or to detachment of the bogie from the 

aeroplane, or to MLG collapse, possibly 

resulting in damage to the aeroplane and 

injury to the occupants. 

To enable early detection and repair of 

corrosion of the internal surfaces, EASA 

issued EASA AD 2007–0314 to require a onetime inspection of all MLG bogie beams, 

except Enhanced MLG bogie beams, and the 

reporting of the results to Airbus. EASA AD 

2007–0314 was revised and later superseded 

by EASA AD 2008–0093, reducing the 

inspection threshold period. 

The results of subsequent investigations 

showed thin paint coats and paint 

degradation, confirmed as well on Enhanced 

MLG bogie beams. To address this additional 

concern, EASA issued AD 2011–0141 [which 

was not mandated by the FAA], retaining the 

requirements of EASA AD 2008–0093, which 

was superseded, to require a one-time visual 

inspection of all MLG bogie beams, including 

a visual examination of the internal diameter 

for corrosion or damage to protective 

treatments of the bogie beam and 

measurement of the paint thickness on the 

internal bore, accomplishment of the 

applicable corrective actions and a 

modification of the MLG bogie beam to 

improve the coat paint application method, 

and application of corrosion protection. 

Prompted by in-service requests, EASA 

issued EASA AD 2012–0015 retaining the 

requirements of EASA AD 2011–0141, which 

was superseded, and introducing repetitive 

inspections of the MLG bogie beams, which 

allows extension of the compliance time for 

the MLG bogie beam modification from 15 

years to 21 years. Modification of a MLG 

bogie beam constitutes terminating action for 

the repetitive inspections for that MLG bogie 

beam. 

Reports on inspection results provided to 

Airbus show that some aeroplanes were 

initially inspected too early (before 4 years 

and 6 months since aeroplane first flight with 

bogie beam installed/installed after overhaul) 

and have not been re-inspected as required. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2012–0015, which is superseded, and 

redefines the inspection periodicity. This 

[EASA] AD also introduces a specific onetime inspection for aeroplanes that have been 

inspected too early. 

Prompted by operator comments, this 

[EASA] AD is revised to clarify the required 

actions and the specific configurations to 

which the actions must be applied. Appendix 

1 of this [EASA] AD has been amended 

accordingly. 

This [EASA] AD is republished to 

editorially correct paragraph (4). 

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–2013– 

0828. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the second SNPRM and the 

FAA’s response. 

Request To Revise the Applicability of 

the Second SNPRM 

American Airlines (AAL) requested 

that we revise the applicability of the 

proposed AD (in the second SNPRM) to 

exclude airplanes with MLG bogie 

beams that have had Airbus 

modification 58896 embodied inservice, as specified in Airbus Service 

Bulletin A330–32–3237. AAL pointed 

out that paragraph (c) of the proposed 

AD (in the second SNPRM) does not 

reflect MLG bogie beams that were 

modified in-service. 

We disagree with the request to revise 

the applicability of the proposed AD (in 

the second SNPRM). Paragraph (k) of 

this AD specifically requires inspection, 

repair, modification, and reidentification of the MLG bogie beams. 

However, paragraph (f) of this AD states 

that actions already done need not be 

repeated. If an operator has already 

accomplished the actions required by 

paragraph (k) of this AD before the 

effective date of this AD, then the 

modified airplane is already in 

compliance with the corresponding 

requirements of this AD. We have not 

made any changes to this AD in this 

regard. 

Additional Changes Made in This AD 

We have revised paragraph (m)(1) of 

this AD to remove reference to 

paragraph (g) of this AD; the reporting 

requirement specified in paragraph 

(m)(1) of this AD is required only for the 


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inspection required by paragraph (k) of 

this AD. 

We have also revised paragraph (m)(2) 

of this AD to reference the correct 

service information for reporting 

inspection findings for the inspection 

required by paragraph (h) of this AD. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the second SNPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the second SNPRM. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. 

• Airbus Service Bulletin A330–32– 

3225, Revision 02, including Appendix 

1, dated October 26, 2012. This service 

information describes procedures for 

cleaning the internal bore and 

accomplishing a detailed inspection of 

internal surfaces of the left-hand (LH) 

and right-hand (RH) MLG bogie beams 

to detect any damage to the protective 

treatments and any corrosion, and 

measuring the paint thickness on the 

internal bore. 

• Airbus Service Bulletin A330–32– 

3237, Revision 01, including Reporting 

Sheet, dated October 14, 2011. This 

service information describes 

procedures for a detailed inspection for 

damage and corrosion of the internal 

bores of the LH and RH MLG bogie 

beam and repair, as well as modification 

and re-identification. 

• Airbus Service Bulletin A340–32– 

4268, Revision 03, including Appendix 

1, dated January 14, 2013. This service 

information describes procedures for 

cleaning the internal bore and 

accomplishing a detailed inspection of 

internal surfaces of the LH and RH MLG 

bogie beams to detect any damage to the 

protective treatments and any corrosion, 

and measuring the paint thickness on 

the internal bore. 

• Airbus Service Bulletin A340–32– 

4279, Revision 01, including Reporting 

Sheet, dated October 14, 2011. This 

service information describes 

procedures for a detailed inspection for 

damage and corrosion of the internal 

bores of the LH and RH MLG bogie 

beam, repair, modification, and 

reidentification. 

Messier-Bugatti-Dowty has issued the 

following service information. 

• Messier-Dowty Service Bulletin 

A33/34–32–278, Revision 1, including 

Appendixes A and B, dated August 24, 

2011. This service information describes 

procedures for inspections for damage 

and corrosion to the protective 

treatment of the internal bores of the LH 

and RH MLG bogie beam, and repairs. 

• Messier-Dowty Service Bulletin 

A33/34–32–283, Revision 1, including 

Appendix A, dated July 10, 2012. This 

service information describes 

procedures for modification of the LH 

and RH MLG bogie beams. 

• Messier-Dowty Service Bulletin 

A33/34–32–284, Revision 1, including 

Appendix A, dated July 10, 2012. This 

service information describes 

procedures for modification of the LH 

and RH MLG bogie beams. 

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. 

Costs of Compliance 

We estimate that this AD affects 51 

airplanes of U.S. registry. 

We also estimate that it takes about 34 

work-hours per product to comply with 

this AD, and 1 work-hour per product 

for reporting. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $151,725, or 

$2,975 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 10 work-hours at a labor rate of 

$85 per work-hour, for a cost of $850 

per product. We have no way of 

determining the number of aircraft that 

might need these actions. 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 


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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) 

2009–15–17, Amendment 39–15980 (74 

FR 37523, July 29, 2009), and adding the 

following new AD: 

2016–18–07 Airbus: Amendment 39–18637; 

Docket No. FAA–2013–0828; Directorate 

Identifier 2012–NM–036–AD. 

(a) Effective Date 

This AD is effective November 2, 2016. 

(b) Affected ADs 

This AD replaces AD 2009–15–17, 

Amendment 39–15980 (74 FR 37523, July 29, 

2009) (‘‘AD 2009–15–17’’). 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category, all manufacturer 

serial numbers (MSN), except those on which 

Airbus modification 58896 has been 

embodied in production. 

(1) Airbus Model A330–223F, –243F, –201, 

–202, –203, –223, –243, –301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes. 

(2) Airbus 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 thin 

paint coats and paint degradation on 

enhanced main landing gear (MLG) bogie 

beams, as well as reports that some airplanes 

have been inspected too early and not reinspected as needed. We are issuing this AD 

to detect and correct damage or corrosion of 

the MLG bogie beams, which could cause a 

runway excursion event, bogie beam 

detachment from the airplane, or MLG 

collapse, and could result in damage to the 

airplane and injury to the occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections for Certain 

Airplane Configurations 

For airplanes equipped with basic MLG 

(201252 series), or growth MLG (201490 

series): After 54 months at the earliest, but no 

later than 72 months since the left-hand (LH) 

or right-hand (RH) MLG bogie beam’s first 

flight on an airplane, or since its first flight 

on an airplane after overhaul, as applicable, 

clean the internal bore and accomplish a 

detailed inspection of internal surfaces of the 

LH and RH MLG bogie beams to detect any 

damage to the protective treatments and any 

corrosion, and measure the paint thickness 

on the internal bore, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3225, Revision 02, 

including Appendix 1, dated October 26, 

2012; or Airbus Service Bulletin A340–32– 

4268, Revision 03, including Appendix 1, 

dated January 14, 2013; as applicable. Repeat 

the inspections thereafter at intervals not less 

than 54 months, but not exceeding 72 

months, after the most recent inspection. 

During overhaul of a MLG bogie beam, any 

corrosion will be removed, which means that 

the first inspection after overhaul of that 

MLG bogie beam, as required by this 

paragraph, is between 54 months and 72 

months since its first flight on an airplane 

after overhaul. 

(h) One-Time Detailed Inspection for Certain 

Airplane Configurations 

For airplanes equipped with basic MLG 

(201252 series), or growth MLG (201490 

series) having a LH or RH MLG bogie beam 

that has already exceeded 72 months since its 

first flight on an airplane, or since its first 

flight on an airplane after overhaul, as 

applicable, as of the effective date of this AD; 

and that has been inspected as specified in 

Airbus Service Bulletin A330–32–3225 or 

Airbus Service Bulletin A340–32–4268, as 

applicable, earlier than 54 months since first 

flight of the affected MLG bogie beam on an 

airplane, or since its first flight on an 

airplane after its most recent overhaul, as 

applicable: Within the applicable compliance 

time indicated in paragraphs (h)(1) through 

(h)(4) of this AD, clean the internal bore and 

accomplish a detailed inspection of the 

internal surfaces of the LH and RH MLG 

bogie beams to detect any damage to the 

protective treatments and any corrosion, and 

measure the paint thickness on the internal 

bore, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3225, Revision 02, 

including Appendix 1, dated October 26, 

2012; or Airbus Service Bulletin A340–32– 

4268, Revision 03, including Appendix 1, 

dated January 14, 2013; as applicable. 

(1) For MLG bogie beams having the 

configurations specified in both paragraphs 

(h)(1)(i) and (h)(1)(ii) of this AD: Do the 

detailed inspection specified in the 

introductory text of paragraph (h) of this AD 

within 9 months after the effective date of 

this AD. 

(i) MLG bogie beams having between 72 

and 120 months since first flight on an 

airplane, or since the MLG bogie beam’s first 

flight on an airplane after the MLG bogie 

beam’s most recent overhaul, as applicable. 

(ii) MLG bogie beams on which the first 

inspection was done after 51 months and 

before 54 months since first flight of the MLG 

bogie beam on an airplane, or since the MLG 

bogie beam’s first flight on an airplane after 

the MLG bogie beam’s most recent overhaul, 

as applicable. 

(2) For MLG bogie beams having the 

configurations specified in both paragraphs 

(h)(2)(i) and (h)(2)(ii) of this AD: Do the 

detailed inspection specified in the 

introductory text of paragraph (h) of this AD 

within 3 months after the effective date of 

this AD. 

(i) MLG bogie beams having between 72 

and 120 months since first flight on an 

airplane, or since the MLG bogie beam’s first 

flight on an airplane after the MLG bogie 

beam’s most recent overhaul, as applicable. 

(ii) MLG bogie beams on which the first 

inspection was done after 45 months and 

before 51 months since first flight of the MLG 

bogie beam on an airplane, or since the MLG 

bogie beam’s first flight on an airplane after 

the MLG bogie beam’s most recent overhaul, 

as applicable. 

(3) For MLG bogie beams having the 

configurations specified in both paragraphs 

(h)(3)(i) and (h)(3)(ii) of this AD: Do the 

detailed inspection specified in the 

introductory text of paragraph (h) of this AD 

within 3 months after the effective date of 

this AD. 

(i) MLG bogie beams having between 72 

and 96 months since first flight on an 

airplane, or since the MLG bogie beam’s first 

flight on an airplane after the MLG bogie 

beam’s most recent overhaul, as applicable. 

(ii) MLG bogie beams which have 

accumulated, at the effective date of this AD, 

less than 96 months and on which the first 

inspection was done before 51 months since 

first flight of the MLG bogie beam on an 

airplane, or since the MLG bogie beam’s first 

flight on an airplane after the after the MLG 

bogie beam’s most recent overhaul, as 

applicable. 

(4) For MLG bogie beams having the 

configurations specified in both paragraphs 

(h)(4)(i) and (h)(4)(ii) of this AD: Do the 

detailed inspection specified in the 

introductory text of paragraph (h) of this AD 

within 1 month after the effective date of this 

AD. 

(i) MLG bogie beams having between 96 

and 120 months since first flight on an 

airplane, or since the MLG bogie beam’s first 

flight on an airplane after the MLG bogie 

beam’s most recent overhaul, as applicable. 

(ii) MLG bogie beams which has 

accumulated, at the effective date of this AD, 

96 months or more and on which the first 

inspection was done before 45 months since 

first flight of the MLG bogie beam on an 

airplane, or since the MLG bogie beam’s first 

flight on an airplane after the MLG bogie 

beam’s most recent overhaul, as applicable. 

(i) Application of Protective Treatment 

If, during any inspection required by 

paragraph (g) or (h) of this AD, no damage 

or corrosion is found: Before further flight, 

apply the protective treatments to the MLG 

bogie beam, in accordance with the 

Accomplishment Instructions of MessierDowty Service Bulletin A33/34–32–272, 

Revision 1, including Appendixes A, B, C, 

and D, dated September 22, 2008. 

(j) Repair and Application of Protective 

Treatment 

If, during any inspection required by 

paragraph (g) or (h) of this AD, any damage 

or corrosion is found: Before further flight, 

repair and apply the protective treatments to 

the MLG bogie beam, in accordance with the 

Accomplishment Instructions of MessierDowty Service Bulletin A33/34–32–272, 

Revision 1, including Appendixes A, B, C, 

and D, dated September 22, 2008. 


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66522 Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations 

(k) Inspection and Corrective Actions 

For airplanes equipped with basic MLG 

(201252 series), growth MLG (201490 series), 

or enhanced MLG (10–210 series): Before the 

accumulation of 252 total months on an MLG 

bogie beam, or within 90 days after the 

effective date of this AD, whichever occurs 

later, do the actions specified in paragraphs 

(k)(1) and (k)(2) of this AD concurrently and 

in sequence. 

(1) Except as provided by paragraph (k)(3) 

of this AD: Do a detailed inspection for 

damage and corrosion of the internal bores of 

the LH and RH MLG bogie beam, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

32–3237 or A340–32–4279, both Revision 01, 

both including Reporting Sheet, both dated 

October 14, 2011, as applicable. If any 

damage or corrosion is found, before further 

flight, repair in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3237 or A340–32– 

4279, both Revision 01, both including 

Reporting Sheet, both dated October 14, 

2011, as applicable. 

(2) Except as provided by paragraph (k)(3) 

of this AD: Modify and re-identify, as 

applicable, the LH and RH MLG bogie beams, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

32–3237 or A340–32–4279, both Revision 01, 

both including Reporting Sheet, both dated 

October 14, 2011, as applicable. 

(3) The inspection requirements of 

paragraph (k)(1) of this AD, and the 

modification requirements only of paragraph 

(k)(2) of this AD, do not apply to any MLG 

bogie beam with a serial number listed in 

Appendix A of Messier-Dowty Service 

Bulletin A33/34–32–283 or A33/34–32–284, 

both Revision 1, both dated July 10, 2012, as 

applicable. 

(l) Optional Methods of Compliance for 

Certain Airplane Configurations 

Inspections and corrective actions on both 

MLG bogie beams done in accordance with 

the instructions of Messier-Dowty Service 

Bulletin A33/34–32–271, Revision 1, 

including Appendixes A and B, dated 

November 16, 2007; or Messier-Dowty 

Service Bulletin A33/34–32–272, Revision 1, 

including Appendixes A, B, C, and D, dated 

September 22, 2008; as applicable; are 

acceptable methods of compliance for the 

requirements of paragraph (g) of this AD, 

provided each inspection is accomplished 

between 54 months and 72 months since the 

first flight of the affected MLG bogie beam on 

an airplane, or since the MLG bogie beam’s 

first flight after the MLG bogie beam’s most 

recent overhaul, as applicable. 

(m) Reporting Requirement 

(1) Submit a report of the findings (both 

positive and negative) of each inspection 

required by paragraph (k) of this AD, as 

applicable, to Airbus, Customer Service 

Directorate, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France, using the 

applicable Reporting Sheet in Airbus Service 

Bulletin A330–32–3237, Revision 01, 

including Reporting Sheet, dated October 14, 

2011; or Airbus Service Bulletin A340–32– 

4279, Revision 01, including Reporting 

Sheet, dated October 14, 2011; at the 

applicable time specified in paragraph 

(m)(1)(i) or (m)(1)(ii) of this AD. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 90 days after the inspection. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 90 days after the effective date of this 

AD. 

(2) Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (h) of this AD to 

Airbus, Customer Service Directorate, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France, using the applicable 

Reporting Sheet in Airbus Service Bulletin 

A330–32–3225, Revision 02, including 

Appendix 1, dated October 26, 2012; or 

Airbus Service Bulletin A340–32–4268, 

Revision 03, including Appendix 1, dated 

January 14, 2013; at the applicable time 

specified in paragraph (m)(2)(i) or (m)(2)(ii) 

of this AD. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(n) Optional Method of Compliance for 

Certain Requirements 

(1) Inspections for damage and corrosion to 

the protective treatment of the internal bores 

of the LH and RH MLG bogie beam, and 

repairs, done in accordance with MessierDowty Service Bulletin A33/34–32–278, 

Revision 1, including Appendixes A and B, 

dated August 24, 2011, are acceptable 

methods of compliance with the 

corresponding requirements of paragraph 

(k)(1) of this AD. 

(2) Modification of the LH and RH MLG 

bogie beams, done in accordance with 

Messier-Dowty Service Bulletins A33/34–32– 

283 or A33/34–32–284, both Revision 1, both 

including Appendix A, both dated July 10, 

2012, as applicable, is an acceptable method 

of compliance with the corresponding 

requirements of paragraph (k)(2) of this AD. 

(o) Optional Terminating Action for Certain 

Requirements 

Modification of both LH and RH MLG 

bogie beams on an airplane, done in 

accordance with paragraph (k) of this AD, or 

as specified in paragraphs (n)(1) and (n)(2) of 

this AD, terminates the repetitive inspections 

required by paragraph (g) of this AD for this 

airplane. 

(p) Credit for Previous Actions 

(1) This paragraph provides credit for the 

corresponding inspections and corrective 

actions done on an LH or RH MLG bogie 

beam required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A330–32–3225, dated November 21, 

2007; or Revision 1, dated October 30, 2008; 

provided the inspections and corrective 

actions were accomplished between 54 

months and 72 months since first flight of the 

affected MLG bogie beam on an airplane, or 

since its first flight after the MLG bogie 

beam’s most recent overhaul, as applicable. 

Airbus Service Bulletin A330–32–3225, 

dated November 21, 2007, is not incorporated 

by reference in this AD. Airbus Mandatory 

Service Bulletin A330–32–3225, Revision 01, 

including Appendix 1, dated October 30, 

2008, was incorporated by reference in AD 

2009–15–07. 

(2) This paragraph provides credit for the 

corresponding inspections and corrective 

actions done on an LH or RH MLG bogie 

beam required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus 

Mandatory Service Bulletin A340–32–4268, 

dated November 21, 2007; Revision 01, 

including Appendix 1, dated October 30, 

2008; or Revision 02, dated October 26, 2012; 

provided these inspections and corrective 

actions were accomplished between 54 

months and 72 months since first flight of the 

affected MLG bogie beam on an airplane, or 

since its first flight after the MLG bogie 

beam’s most recent overhaul, as applicable. 

Airbus Service Bulletin A340–32–4268, 

dated November 21, 2007; and Revision 02, 

dated October 26, 2012; are not incorporated 

by reference in this AD. Airbus Mandatory 

Service Bulletin A340–32–4268, Revision 01, 

including Appendix 1, dated October 30, 

2008, was incorporated by reference in AD 

2009–15–17. 

(3) This paragraph provides credit for the 

corresponding actions required by paragraph 

(n)(1) of this AD, if those actions were 

performed before the effective date of this AD 

using Messier-Dowty Service Bulletin A33/ 

34–32–271, dated September 13, 2007, which 

is not incorporated by reference in this AD. 

(4) This paragraph provides credit for the 

corresponding actions required by 

paragraphs (j) and (n)(1) of this AD, if those 

actions were performed before the effective 

date of this AD using Messier-Dowty Service 

Bulletin A33/34–32–272, including 

Appendixes A, B, C, and D, dated November 

16, 2007, which is not incorporated by 

reference in this AD. 

(5) This paragraph provides credit for the 

corresponding actions required by 

paragraphs (k), (m), and (r)(1)(i) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A330–32–3237, including Reporting 

Sheet, dated January 18, 2011. 

(6) This paragraph provides credit for the 

corresponding actions required by 

paragraphs (k), (m), and (r)(1)(i) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A340–32–4279, including Reporting 

Sheet, dated January 18, 2011. 

(7) This paragraph provides credit for the 

corresponding actions required by 

paragraphs (k)(3), (n)(2), (r)(1)(ii), and 

(r)(1)(iii) of this AD, if those actions were 

performed before the effective date of this AD 

using Messier-Dowty Service Bulletin A33/ 

34–32–283, including Appendix A, dated 

May 11, 2010, which is not incorporated by 

reference in this AD. 

(8) This paragraph provides credit for the 

corresponding actions required by 

paragraphs (k)(3), (n)(2), (r)(1)(ii), and 

(r)(1)(iii) of this AD, if those actions were 

performed before the effective date of this AD 


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Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations 66523 

using Messier-Dowty Service Bulletin A33/ 

34–32–284, including Appendix A, dated 

May 11, 2010, which is not incorporated by 

reference in this AD. 

(9) This paragraph provides credit for the 

corresponding actions required by 

paragraphs (n)(1) and (r)(1)(ii) of this AD, if 

those actions were performed before the 

effective date of this AD using Messier-Dowty 

Service Bulletin A33/34–32–278, including 

Appendixes A and B, dated February 17, 

2010, which is not incorporated by reference 

in this AD. 

(q) Clarification of Inspection Compliance 

Times 

After accomplishment of the one-time 

detailed inspection required by paragraph (h) 

of this AD, the repetitive actions required by 

paragraph (g) of this AD remain applicable, 

and must be done within the compliance 

times specified in paragraph (g) of this AD. 

(r) Parts Installation Limitations 

(1) After modification of an airplane, as 

required by paragraph (k) of this AD, or as 

specified in paragraphs (n)(1) and (n)(2) of 

this AD, do not install an MLG bogie beam 

on any airplane unless it is done in 

compliance with the requirements of 

paragraph (r)(1)(i), (r)(1)(ii), or (r)(1)(iii) of 

this AD. 

(i) The MLG bogie beam has been modified 

and re-identified in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3237 or A340–32– 

4279, both Revision 01, both including 

Reporting Sheet, both dated October 14, 

2011, as applicable. 

(ii) The MLG bogie beam has been 

inspected and all applicable corrective 

actions have been done in accordance with 

the Accomplishment Instructions of MessierDowty Service Bulletin A33/34–32–278, 

Revision 1, dated August 24, 2011; and 

modified in accordance with the 

Accomplishment Instructions of MessierDowty Service Bulletin A33/34–32–283 or 

A33/34–32–284, both Revision 1, both 

including Appendix A, both dated July 10, 

2012. 

(iii) The MLG bogie beam has a serial 

number listed in Appendix A of MessierDowty Service Bulletin A33/34–32–283 or 

A33/34–32–284, both Revision 1, both dated 

July 10, 2012, as applicable. 

(2) As of the effective date of this AD, 

except as specified in paragraph (r)(1) of this 

AD, installation of an MLG bogie beam on an 

airplane is allowed, provided that following 

the installation it is inspected and all 

applicable repairs and corrective actions 

have been done in accordance with the 

requirements of this AD. 

(s) 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. 

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. 

(3) 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 

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. 

(t) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) AD 2013– 

0267R1, dated March 4, 2014; corrected 

March 8, 2014, 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– 

2013–0828. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (u)(5), (u)(6), and (u)(7) of this 

AD. 

(u) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on November 2, 2016. 

(i) Airbus Service Bulletin A330–32–3225, 

Revision 02, including Appendix 1, dated 

October 26, 2012. 

(ii) Airbus Service Bulletin A330–32–3237, 

Revision 01, including Reporting Sheet, 

dated October 14, 2011. 

(iii) Airbus Service Bulletin A340–32– 

4268, Revision 03, including Appendix 1, 

dated January 14, 2013. 

(iv) Airbus Service Bulletin A340–32– 

4279, Revision 01, including Reporting 

Sheet, dated October 14, 2011. 

(v) Messier-Dowty Service Bulletin A33/ 

34–32–278, Revision 1, including 

Appendixes A and B, dated August 24, 2011. 

(vi) Messier-Dowty Service Bulletin A33/ 

34–32–283, Revision 1, including Appendix 

A, dated July 10, 2012. 

(vii) Messier-Dowty Service Bulletin A33/ 

34–32–284, Revision 1, including Appendix 

A, dated July 10, 2012. 

(4) The following service information was 

approved for IBR on September 2, 2009 (74 

FR 37523, July 29, 2009). 

(i) Messier-Dowty Service Bulletin A33/ 

34–32–271, Revision 1, including 

Appendixes A and B, dated November 16, 

2007. 

(ii) Messier-Dowty Service Bulletin A33/ 

34–32–272, Revision 1, including 

Appendixes A, B, C, and D, dated September 

22, 2008. 

(5) 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. 

(6) For Messier-Dowty service information 

identified in this AD, contact Messier-Dowty: 

Messier Services Americas, Customer 

Support Center, 45360 Severn Way, Sterling, 

VA 20166–8910; telephone 703–450–8233; 

fax 703–404–1621; Internet: https://

techpubs.services/messier-dowty.com. 

(7) 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. 

(8) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on August 

24, 2016. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–21150 Filed 9–27–16; 8:45 am] 

BILLING CODE 4910–13–P 


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