44994 Federal Register / Vol. 81, No. 133 / Tuesday, July 12, 2016 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–0459; Directorate 

Identifier 2015–NM–081–AD; Amendment 

39–18589; AD 2016–14–08] 

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) 2015–10– 

03 for certain Airbus Model A330–200 

and –300 series airplanes, and Model 

A340–200 and –300 series airplanes. AD 

2015–10–03 required a detailed 

inspection for visible chrome of each 

affected main landing gear (MLG) 

sidestay upper cardan pin, associated 

nuts, and retainer assembly; pin 

replacement if needed; measurement of 

cardan pin clearance dimensions (gap 

check); corrective actions if necessary; 

and a report of all findings. This new 

AD requires a detailed inspection of the 

upper cardan pin and nut threads for 

any corrosion, pitting, or thread damage, 

and if necessary, replacement of the 

cardan pin and nut. This new AD also 

revises the applicability to include 

additional airplane models. This AD 

was prompted by a report that an MLG 

sidestay upper cardan pin migration 

event had been caused by corrosion due 

to lack of jointing compound and 

inadequate sealant application during 

the MLG installation. We are issuing 

this AD to detect and correct migration 

of the sidestay upper cardan pin, which 

could result in disconnection of the 

sidestay upper arm from the airplane 

structure, and could result in a landing 

gear collapse and consequent damage to 

the airplane and injury to occupants. 

DATES: This AD is effective August 16, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 16, 2016. 

ADDRESSES: For 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. 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–2016–0459. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

0459; 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 800–647–5527) 

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 notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2015–10–03, 

Amendment 39–18158 (80 FR 30608, 

May 29, 2015) (‘‘AD 2015–10–03’’). AD 

2015–10–03 applied to certain Airbus 

Model A330–200 and –300 series 

airplanes, and Model A340–200 and 

–300 series airplanes. The NPRM 

published in the Federal Register on 

January 21, 2016 (81 FR 3346) (‘‘the 

NPRM’’). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2015–0079, dated May 7, 2015 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

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

condition for certain Airbus Model 

A330–200 and –300 series airplanes, 

Model A340–200 and –300 series 

airplanes, and Model A340–541 and 

–642 airplanes. The MCAI states: 

An A330 aeroplane equipped with Basic 

MLG was rolling out after landing when it 

experienced a nose wheel steering fault 

(unrelated to the safety subject addressed by 

this AD), which resulted in the crew stopping 

the aeroplane on the taxiway after vacating 

the runway. The subsequent investigation 

revealed that the right-hand MLG sidestay 

upper cardan pin had migrated out of 

position. The sidestay upper cardan nut and 

retainer had detached from the upper cardan 

pin and were found, still bolted together, in 

the landing gear bay. 

Prompted by these findings, Airbus 

published Alert Operators Transmission 

(AOT) A32L003–14, providing inspection 

instructions and, as an interim solution, 

EASA issued AD 2014–0066 [which 

corresponds to FAA AD 2015–10–03, 

Amendment 39–18158 (80 FR 30608, May 29, 

2015)] to require repetitive detailed 

inspections (DET) of the MLG upper cardan 

pin, nut and retainer. That AD also required 

accomplishment of a one-time gap check 

between wing rear spar fitting lugs and the 

bush flanges and, depending on findings, 

corrective action(s). The gap check (including 

corrections, as necessary) terminated the 

repetitive DET. 

Since that [EASA] AD was issued, further 

investigation concluded that the reported 

MLG sidestay upper cardan pin migration 

event had been caused by corrosion, due to 

lack of jointing compound and inadequate 

sealant application during MLG installation. 

Therefore, this issue affects any MLG that 

had an upper cardan pin replacement or reinstallation, irrespective of MLG overhaul. 

Any corrosion on the upper cardan pin and 

nut threads would not have been detected 

during the previously required DET. 

This condition, if not detected and 

corrected, could lead to a complete migration 

of the sidestay upper cardan pin and a 

disconnection of the sidestay upper arm from 

the aeroplane structure, possibly resulting in 

MLG collapse with consequent damage to the 

aeroplane and injury to occupants. 

To address this potential unsafe condition, 

Airbus published Service Bulletin (SB) 

A330–32–3269, SB A340–32–4301 and SB 

A340–32–5115 providing inspection 

instructions. In addition, to prevent any 

improper re-installation of an upper cardan 

pin on a MLG, Airbus amended the 

applicable Aircraft Maintenance Manual 

(AMM) on 01 October 2014. 

For the reasons described above, this 

[EASA] AD supersedes EASA [AD] 2014– 

0066 and requires a one-time DET of the 

MLG upper cardan pin and nut threads to 

check for corrosion or damage on the upper 

cardan pin and nut threads, and, depending 

on findings, replacement of the damaged 

part(s). 

As this unsafe condition could also 

develop on A330 freighters and A340–500/ 

–600 aeroplanes, this [EASA] AD also applies 

to those aeroplanes. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

0459. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM and the FAA’s 

response to that comment. 

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Federal Register / Vol. 81, No. 133 / Tuesday, July 12, 2016 / Rules and Regulations 44995 

Request To Use the Latest Service 

Information 

American Airlines (AA) requested 

that we use the latest service 

information in the NPRM. AA stated 

that since the NPRM was issued, Airbus 

released Service Bulletin A330–32– 

3269, Revision 01, dated December 3, 

2015. 

We agree with the commenter for the 

reasons stated above. We have reviewed 

Airbus Service Bulletin A330–32–3269, 

Revision 01, dated December 3, 2015, 

and there are no substantial changes. In 

addition, we have also reviewed Airbus 

Service Bulletin A340–32–4301, 

Revision 01, dated December 3, 2015; 

and Airbus Service Bulletin A340–32– 

5115, Revision 01, dated December 11, 

2015. There are no substantial changes. 

We have revised this AD accordingly. 

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 changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information: 

• Airbus Service Bulletin A330–32– 

3269, Revision 01, dated December 3, 

2015. 

• Airbus Service Bulletin A340–32– 

4301, Revision 01, dated December 3, 

2015. 

• Airbus Service Bulletin A340–32– 

5115, Revision 01, dated December 

11, 2015. 

The service information describes 

procedures for a detailed inspection of 

the upper cardan pin and nut threads 

for any corrosion, pitting, or thread 

damage, and replacement of the cardan 

pin and nut. 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 95 

airplanes of U.S. registry. 

We also estimate that it will take 

about 11 work-hours per product to 

comply with the basic requirements of 

this AD. 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 $88,825, or $935 per 

product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 12 work-hours and require parts 

costing $78,136, for a cost of $79,156 

per product. We have no way of 

determining the number of aircraft that 

might need this action. 

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: 

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) 

2015–10–03, Amendment 39–18158 (80 

FR 30608, May 29, 2015), and adding 

the following new AD: 

2016–14–08 Airbus: Amendment 39–18589. 

Docket No. FAA–2016–0459; Directorate 

Identifier 2015–NM–081–AD. 

(a) Effective Date 

This AD is effective August 16, 2016. 

(b) Affected ADs 

This AD replaces 2015–10–03, Amendment 

39–18158 (80 FR 30608, May 29, 2015). 

(c) Applicability 

This AD applies to the airplanes, 

certificated in any category, identified in 

paragraphs (c)(1), (c)(2), and (c)(3) of this AD, 

except airplanes on which an upper cardan 

pin on a main landing gear (MLG) has never 

been replaced or reinstalled since first entry 

into service of the airplane. 

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

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

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

airplanes, all manufacturer serial numbers. 

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

–311, –312, and –313 airplanes, all 

manufacturer serial numbers. 

(3) Airbus Model A340–541 and –642 

airplanes, all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by a report that an 

MLG sidestay upper cardan pin migration 

event had been caused by corrosion due to 

lack of jointing compound and inadequate 

sealant application during the MLG 

installation. We are issuing this AD to detect 

and correct migration of the sidestay upper 

cardan pin, which could result in 

disconnection of the sidestay upper arm from 

the airplane structure, and could result in a 

landing gear collapse and consequent damage 

to the airplane and injury to occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definition 

For the purpose of this AD, an upper 

cardan pin on a MLG is affected if it has been 

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44996 Federal Register / Vol. 81, No. 133 / Tuesday, July 12, 2016 / Rules and Regulations 

installed as a replacement part, or reinstalled 

since first entry of the airplane into service, 

and if the installation was accomplished 

using the applicable airplane maintenance 

manual at a revision level prior to October 1, 

2014. 

(h) Inspection and Replacement 

(1) For an affected upper cardan pin on an 

MLG: Before exceeding 96 months since its 

latest installation on an airplane, or within 

12 months after the effective date of this AD, 

whichever occurs later, do a detailed 

inspection of the upper cardan pin and nut 

threads for any corrosion, pitting, or thread 

damage, in accordance with the 

Accomplishment Instructions of the 

applicable service information specified in 

paragraph (i) of this AD. 

(2) If, during the detailed inspection 

specified in paragraph (h)(1) of this AD, any 

corrosion, pitting, or thread damage is found, 

before further flight, replace the upper cardan 

pin and/or nut, as applicable, in accordance 

with the Accomplishment Instructions of the 

applicable service information specified in 

paragraph (i) of this AD. 

(i) Applicable Service Information 

Do the actions required by paragraph (h) of 

this AD in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraphs (i)(1), (i)(2), and (i)(3) of this AD. 

(1) Airbus Service Bulletin A330–32–3269, 

Revision 01, dated December 3, 2015 (for 

Airbus Model A330–201, –202, –203, –223, 

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

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

(2) Airbus Service Bulletin A340–32–4301, 

Revision 01, dated December 3, 2015 (for 

Airbus Model A340–211, –212, –213, –311, 

–312, and –313 airplanes). 

(3) Airbus Service Bulletin A340–32–5115, 

Revision 01, dated December 11, 2015 (for 

Airbus Model A340–541 and –642 airplanes). 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using the applicable 

service information identified in paragraphs 

(j)(1), (j)(2), and (j)(3) of this AD. This service 

information is not incorporated by reference 

in this AD. 

(1) Airbus Service Bulletin A330–32–3269, 

dated February 17, 2015. 

(2) Airbus Service Bulletin A340–32–4301, 

dated February 17, 2015. 

(3) Airbus Service Bulletin A340–32–5115, 

dated February 17, 2015. 

(k) 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. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0079, dated 

May 7, 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– 

2016–0459. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(m) 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) Airbus Service Bulletin A330–32–3269, 

Revision 01, dated December 3, 2015. 

(ii) Airbus Service Bulletin A340–32–4301, 

Revision 01, dated December 3, 2015. 

(iii) Airbus Service Bulletin A340–32– 

5115, Revision 01, dated December 11, 2015. 

(3) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

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

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(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 June 28, 

2016. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–16316 Filed 7–11–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8129; Directorate 

Identifier 2014–NM–197–AD; Amendment 

39–18573; AD 2016–13–09] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2B16 

(CL–604 Variant) airplanes. This AD 

was prompted by a determination that 

certain maintenance tasks for the 

horizontal stabilizer trim actuator 

(HSTA) are inadequate. This AD 

requires revising the maintenance or 

inspection program, as applicable, to 

incorporate new airworthiness 

limitations for the HSTA. We are issuing 

this AD to detect and correct premature 

wear and cracking of the HSTA, which 

could result in failure of the HSTA and 

consequent loss of control of the 

airplane. 

DATES: This AD becomes effective 

August 16, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 16, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Bombardier, Inc., 400 Coˆte-Vertu Road 

West, Dorval, Que ́bec H4S 1Y9, Canada; 

Widebody Customer Response Center, 

toll-free telephone 1–866–538–1247, or 

direct dial telephone 1–514–855–2999; 

fax 1–514–855–7401; email ac.yul@

aero.bombardier.com; Internet http:// 

www.bombardier.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 

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