33368 Federal Register / Vol. 81, No. 102 / Thursday, May 26, 2016 / Rules and Regulations 

(e) Reason 

This AD was prompted by accomplishment 

of a taxi-out checklist which revealed that the 

elevator movement was partially obstructed 

due to rotation of the flight control lock 

adjuster bracket. We are issuing this AD to 

detect and correct discrepancies of the 

elevator tension control regulators. Such a 

condition could result in jamming of the 

elevator mechanism and consequent reduced 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection/Corrective Actions 

At the next scheduled opening of access 

panels 346AB or 346BL after the effective 

date of this AD, but no later than 5,000 flight 

hours after the effective date of this AD: Do 

a one-time detailed inspection of the elevator 

tension control regulator for discrepancies, in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–27–095, dated April 22, 2015. If the 

flight control lock adjuster bracket is found 

loose, any bracket attachment bolt is found 

broken, or any nut is missing, before further 

flight, do all applicable corrective actions in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–27–095, dated April 22, 2015. 

(h) Reporting Requirement 

Submit a report of any positive findings 

during any inspection required by paragraph 

(g) of this AD to Fokker Services B.V., 

Technical Services Dept., P.O. Box 1357, 

2130 EL Hoofddorp, the Netherlands; 

telephone: +31 (0)88–6280–350; fax: +31 

(0)88–6280–111; email: 

technicalservices@fokker.com; Internet 

http://www.myfokkerfleet.com. 

(1) For airplanes on which the inspection 

specified in paragraph (g) of this AD is 

accomplished on or after the effective date of 

this AD: Submit the report within 30 days 

after performing the inspection. 

(2) For airplanes on which the inspection 

specified in paragraph (g) of this AD is 

accomplished before the effective date of this 

AD: Submit the report within 30 days after 

the effective date of this AD. 

(i) 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–227–1137; 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. 

(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, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Fokker B.V. Service’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. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0091, dated 

May 26, 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– 

2015–8430. 

(k) 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) Fokker Service Bulletin SBF100–27– 

095, dated April 22, 2015. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 1357, 

2130 EL Hoofddorp, the Netherlands; 

telephone +31 (0)88–6280–350; fax +31 

(0)88–6280–111; email 

technicalservices@fokker.com; Internet 

http://www.myfokkerfleet.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 May 11, 

2016. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–11930 Filed 5–25–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4815; Directorate 

Identifier 2015–NM–112–AD; Amendment 

39–18522; AD 2016–10–11] 

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) 2015–03– 

06 for all Airbus Model A330–200, 

A330–200 Freighter, A330–300, A340– 

200, A340–300, A340–500, and A340– 

600 series airplanes. AD 2015–03–06 

required repetitive inspections of the 

left-hand (LH) and right-hand (RH) wing 

main landing gear (MLG) rib 6 aft 

bearing lugs (forward and aft) to detect 

any cracks on the two lugs, and 

replacement if necessary. This new AD 

requires reduction of certain compliance 

times. This AD was prompted by reports 

of additional cracking of the MLG rib 6 

aft bearing lugs. We are issuing this AD 

to detect and correct cracking of the 

MLG rib 6 aft bearing lugs, which could 

result in collapse of the MLG upon 

landing. 

DATES: This AD is effective June 30, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 30, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of March 25, 2015 (80 FR 

8511, February 18, 2015). 

ADDRESSES: For service information 

identified in this final rule, contact 


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Federal Register / Vol. 81, No. 102 / Thursday, May 26, 2016 / Rules and Regulations 33369 

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–2015–4815. 

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–2015– 

4815; 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 2015–03–06, 

Amendment 39–18102 (80 FR 8511, 

February 18, 2015) (‘‘AD 2015–03–06’’). 

AD 2015–03–06 applied to all Airbus 

Model A330–200, A330–200 Freighter, 

A330–300, A340–200, A340–300, A340– 

500, and A340–600 series airplanes. The 

NPRM published in the Federal 

Register on November 19, 2015 (80 FR 

72398) (‘‘the NPRM’’). The NPRM was 

prompted by reports of additional 

cracking of the MLG rib 6 aft bearing 

lugs. The NPRM proposed to continue 

to require repetitive inspections of the 

LH and RH wing MLG rib 6 aft bearing 

lugs (forward and aft) to detect any 

cracks on the two lugs at a more 

restrictive initial inspection threshold 

with a grace period for airplanes that 

have already exceeded the new 

threshold; and replacement, if 

necessary. We are issuing this AD to 

detect and correct cracking of the MLG 

rib 6 aft bearing lugs, which could result 

in collapse of the MLG upon landing. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2015–0120, dated June 26, 

2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for all Airbus 

Model A330–200, A330–200 Freighter, 

A330–300, A340–200, A340–300, A340– 

500, and A340–600 series airplanes. The 

MCAI states: 

During Main Landing Gear (MLG) 

lubrication, a crack was visually found in the 

MLG rib 6 aft bearing forward lug on one 

A330 in-service aeroplane. The crack had 

extended through the entire thickness of the 

forward lug at approximately the 4 o’clock 

position (when looking forward). It has been 

determined that a similar type of crack can 

develop on other aeroplane types that are 

listed in the Applicability paragraph. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the MLG attachment. 

To address this situation, Airbus issued 

inspection Service Bulletin (SB) A330–57– 

3096, SB A340–57–4104 and SB A340–57– 

5009 to provide instructions for repetitive 

inspections of the gear rib lugs. 

Prompted by these findings, EASA issued 

Emergency AD 2006–0364–E to require 

repetitive detailed visual inspections of the 

Left Hand (LH) and Right Hand (RH) wing 

MLG rib 6 aft bearing lugs. 

Later, EASA issued AD 2007–0247–E, 

which superseded [EASA] AD 2006–0364–E, 

to: 

—expand the Applicability to all A330 and 

A340 aeroplanes, because the interference 

fit bushes cannot be considered as a 

terminating action, owing to unknown root 

cause; and 

—add a second parameter quoted in flight 

hours (FH) to the inspection interval in 

order to reflect the aeroplane utilisation in 

service. 

EASA AD 2007–0247–E was revised to 

correct a typographical error. 

Since the first crack finding and issuance 

of the inspection SBs and related ADs, six 

further cracks were reported. 

Consequently, EASA issued AD 2013–0271 

[which corresponds to FAA AD 2015–03–06, 

Amendment 39–18102 (80 FR 8511, February 

18, 2015)], which retained the requirements 

of [EASA] AD 2007–0247R1–E, which was 

superseded, and expanded the Applicability 

of the [EASA] AD to the newly certified 

models A330–223F and A330–243F. That 

[EASA] AD also reduced the inspection 

threshold(s) to reflect the updated risk 

assessment and in-service experience. 

Since this [EASA] AD was issued, a new 

occurrence of crack finding was reported. 

Further analysis resulted in the need to 

reduce the threshold of the initial inspection. 

Prompted by this finding, Airbus issued SB 

A330–57–3096 Revision 06 to introduce a 

more restrictive initial inspection threshold 

and a grace period for aeroplanes which have 

already passed the new threshold. 

For the reasons described above, this 

[EASA] AD partially retains the requirements 

of EASA AD 2013–0271, which is 

superseded, and introduces reduced initial 

inspection thresholds. 

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–2015– 

4815. 

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 the comment. 

Request To Reference Unpublished 

Service Information That Terminates 

Repetitive Inspections 

American Airlines requested that we 

add a paragraph to the proposed AD that 

references new service information that 

would terminate the proposed repetitive 

inspections. The commenter stated that 

an Airbus retrofit information letter was 

published indicating that Airbus plans 

to release new service information that 

will terminate the mandatory repetitive 

inspections required by AD 2015–03– 

06. 

We do not agree because the new 

service information is not yet released. 

In an AD, we cannot refer to service 

information that does not exist because 

doing so violates Office of the Federal 

Register (OFR) regulations for approval 

of materials incorporated by reference in 

rules. To allow operators to use service 

information issued after publication of 

an AD, either we must supersede the AD 

to reference specific service 

information, or operators must request 

approval to use the new service 

information as an alternative method of 

compliance with the AD under the 

provisions of paragraph (k) of this AD. 

We have not revised this AD in this 

regard. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor 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. 


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Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A330–57–3096, Revision 06, dated May 

29, 2015. The service information 

describes procedures for detailed 

inspections to detect any cracking on 

the forward and aft lugs of the LH and 

RH wing MLG Rib 6. 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 101 

airplanes of U.S. registry. 

The actions required by AD 2015–03– 

06, and retained in this AD take about 

2 work-hours per product, at an average 

labor rate of $85 per work-hour. Based 

on these figures, the estimated cost of 

the actions that were required by AD 

2015–03–06 is $170 per product. 

The new requirement (reduced 

compliance time) of this AD adds no 

additional economic burden. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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) 

2015–03–06, Amendment 39–18102 (80 

FR 8511, February 18, 2015), and adding 

the following new AD: 

2016–10–11 Airbus: Amendment 39–18522; 

Docket No. FAA–2015–4815; Directorate 

Identifier 2015–NM–112–AD. 

(a) Effective Date 

This AD is effective June 30, 2016. 

(b) Affected ADs 

This AD replaces AD 2015–03–06, 

Amendment 39–18102 (80 FR 8511, February 

18, 2015) (‘‘AD 2015–03–06’’). 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –223, –223F, –243, –243F 

–301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model A340– 

211, –212, –213 –311, –312, –313, –541, and 

–642 airplanes; certificated in any category; 

all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports of 

cracking of the main landing gear (MLG) rib 

6 aft bearing forward lug. We are issuing this 

AD to detect and correct cracking of the MLG 

rib 6 aft bearing lugs, which could result in 

collapse of the MLG upon landing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections 

At the later of the times specified in 

paragraphs (g)(1) and (g)(2) of this AD: Do a 

detailed inspection for cracking of the lefthand and right-hand wing MLG rib 6 aft 

bearing lugs (forward and aft), in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A330–57–3096, 

Revision 06, dated May 29, 2015 (for Model 

A330–201, –202, –203, –223, –223F, –243, 

–243F, –301, –302, –303, –321, –322, –323, 

–341, –342, and –343 airplanes); Airbus 

Service Bulletin A340–57–4104, Revision 04, 

dated October 17, 2013 (for Model A340–211, 

–212, –213, –311, –312, –313 airplanes); or 

Airbus Service Bulletin A340–57–5009, 

Revision 03, dated October 17, 2013 (for 

Model A340–541 and –642 airplanes). 

(1) Within 24 months or 2,000 flight cycles, 

whichever occurs first since airplane first 

flight or since the last MLG support rib 

replacement, as applicable. 

(2) Within 30 days after the effective date 

of this AD. 

(h) Repetitive Inspections 

Repeat the inspection required by 

paragraph (g) of this AD thereafter at the time 

specified in paragraphs (h)(1) through (h)(7) 

of this AD, as applicable. 

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

and –243 airplanes: Repeat the inspections at 

intervals not to exceed 300 flight cycles or 

1,500 flight hours, whichever occurs first. 

(2) For Model A330–223F and –243F 

airplanes: Repeat the inspections at intervals 

not to exceed 300 flight cycles or 900 flight 

hours, whichever occurs first. 

(3) For Model A330–301, –302, –303, –321, 

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

Repeat the inspections at intervals not to 

exceed 300 flight cycles or 900 flight hours, 

whichever occurs first. 

(4) For Model A340–211, –212, and –213 

airplanes: Repeat the inspections at intervals 

not to exceed 200 flight cycles or 800 flight 

hours, whichever occurs first. 

(5) For Model A340–311 and –312 

airplanes; and Model A340–313 airplanes 

(except weight variant (WV) 27): Repeat the 

inspections at intervals not to exceed 200 

flight cycles or 800 flight hours, whichever 

occurs first. 

(6) For Model A340–313 (only WV27) 

airplanes: Repeat the inspections at intervals 

not to exceed 200 flight cycles or 400 flight 

hours, whichever occurs first. 

(7) For Model A340–541 and –642 

airplanes: Repeat the inspections at intervals 

not to exceed 100 flight cycles or 500 flight 

hours, whichever occurs first. 

(i) Corrective Action 

If any crack is found during any inspection 

required by paragraph (g) or (h) of this AD: 

Before further flight, replace the cracked 

MLG support rib 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 


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Organization Approval (DOA). Replacement 

of an MLG support rib does not terminate the 

repetitive inspections required by paragraph 

(h) of this AD. 

(j) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (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) through (j)(15) of this AD. 

(1) Airbus Service Bulletin A330–57A3096, 

dated December 5, 2006, which was 

incorporated by reference in AD 2007–03–04, 

Amendment 39–14915 (72 FR 4416, January 

31, 2007) (‘‘AD 2007–03–04’’). 

(2) Airbus Service Bulletin A330–57A3096, 

Revision 01, dated April 18, 2007, which is 

not incorporated by reference in this AD. 

(3) Airbus Service Bulletin A330–57–3096, 

Revision 02, dated August 13, 2007, which 

was incorporated by reference in AD 2007– 

22–10, Amendment 39–15246 (72 FR 61796, 

November 1, 2007; corrected November 16, 

2007 (72 FR 64532)) (‘‘AD 2007–22–10’’). 

(4) Airbus Service Bulletin A330–57–3096, 

Revision 03, dated October 24, 2012, which 

is not incorporated by reference in this AD. 

(5) Airbus Service Bulletin A330–57–3096, 

Revision 04, dated February 6, 2013, which 

is not incorporated by reference in this AD. 

(6) Airbus Service Bulletin A330–57–3096, 

Revision 05, dated October 17, 2013, which 

was incorporated by reference in AD 2015– 

03–06. 

(7) Airbus Service Bulletin A340–57A4104, 

dated December 5, 2006, which was 

incorporated by reference in AD 2007–03–04. 

(8) Airbus Service Bulletin A340–57–4104, 

Revision 01, dated August 13, 2007, which is 

not incorporated by reference in this AD. 

(9) Airbus Service Bulletin A340–57–4104, 

Revision 02, dated September 5, 2007, which 

was incorporated by reference in AD 2007– 

22–10. 

(10) Airbus Service Bulletin A340–57– 

4104, Revision 03, dated October 24, 2012, 

which is not incorporated by reference in this 

AD. 

(11) Airbus Service Bulletin A340– 

57A5009, dated December 5, 2006, which 

was incorporated by reference in AD 2007– 

03–04. 

(12) Airbus Service Bulletin A340–57– 

5009, Revision 01, dated August 13, 2007, 

which was incorporated by reference in AD 

2007–22–10. 

(13) Airbus Service Bulletin A340–57– 

5009, Revision 02, dated October 24, 2012, 

which is not incorporated by reference in this 

AD. 

(14) Airbus Alert Operators Transmission 

A57L005–14, dated July 15, 2014, which is 

not incorporated by reference in this AD. 

(15) Airbus Alert Operators Transmission 

A57L005–14, Revision 01, dated August 20, 

2014, which is not incorporated by reference 

in this AD. 

(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 EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(3) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0120, dated 

June 26, 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– 

2015–4815. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (m)(5) and (m)(6) 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. 

(3) The following service information was 

approved for IBR on June 30, 2016. 

(i) Airbus Service Bulletin A330–57–3096, 

Revision 06, dated May 29, 2015. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on March 25, 2015 (80 FR 

8511, February 18, 2015). 

(i) Airbus Service Bulletin A340–57–4104, 

Revision 04, dated October 17, 2013. 

(ii) Airbus Service Bulletin A340–57–5009, 

Revision 03, dated October 17, 2013. 

(5) 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. 

(6) 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. 

(7) 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 May 12, 

2016. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–11931 Filed 5–25–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–6892; Directorate 

Identifier 2016–NM–057–AD; Amendment 

39–18529; AD 2016–11–02] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes; Model CL–600–2D15 

(Regional Jet Series 705) airplanes; 

Model CL–600–2D24 (Regional Jet 

Series 900) airplanes; and Model CL– 

600–2E25 (Regional Jet Series 1000) 

airplanes. This AD requires a detailed 

visual inspection of the upper and lower 

engine pylons for protruding, loose, or 

missing fasteners; and repair, including 

applicable related investigative and 

corrective actions, if necessary. This AD 

was prompted by reports of loose or 


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