## 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–


## 66519 Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations

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, EASAissued 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


## 66520 Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations

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:


## 66521 Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations

**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 airplaneshave 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 theAccomplishment 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 theAccomplishment Instructions of MessierDowty Service Bulletin A33/34–32–272, Revision 1, including Appendixes A, B, C, and D, dated September 22, 2008.


## 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, andrepairs, 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


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

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 withthe Accomplishment Instructions of MessierDowty Service Bulletin A33/34–32–278, Revision 1, dated August 24, 2011; and
modified in accordance with theAccomplishment 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 serialnumber 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]

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