This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

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REGISTER issue of each week.

Rules and Regulations Federal Register

52935 

Vol. 80, No. 170 

Wednesday, September 2, 2015 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0085; Directorate 

Identifier 2014–NM–078–AD; Amendment 

39–18255; AD 2015–17–22] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A330–243, A330–243F, 

A330–341, A330–342, and A330–343 

airplanes. This AD was prompted by 

reports indicating that certain hinge 

sleeves on the cowl doors of the thrust 

reverser units (TRUs) were not heat 

treated. This AD requires replacing the 

sleeves of certain hinges on the cowl 

doors of the TRUs with new parts. We 

are issuing this AD to prevent, in the 

event of a fan-blade-off event due to 

high vibration, in-flight loss of TRU 

heavy components, which might 

damage airplane structure or control 

surfaces and consequently reduce 

controllability of the airplane. 

DATES: This AD becomes effective 

October 7, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 7, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-0085 or in 

person at the 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. 

For Airbus service information 

identified in this AD, contact Airbus 

SAS, Airworthiness Office—EAL, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France; telephone +33 5 

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

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. For 

Aircelle service information identified 

in this AD, contact Aircelle Customer 

support Center, BP 50042, 50, rue Pierre 

Curie, 78371 Plaisir Cedex, France: 

telephone +33 (0)1 64 14 80 33; fax +33 

(0)1 64 14 84 10. 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–2015–0085. 

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 by adding an AD that would 

apply to all Airbus Model A330–243, 

A330–243F, A330–341, A330–342, and 

A330–343 airplanes. The NPRM 

published in the Federal Register on 

February 13, 2015 (80 FR 7986). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0062, dated March 11, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for all Airbus 

Model A330–243, A330–243F, A330– 

341, A330–342, and A330–343 

airplanes. The MCAI states: 

A manufacturing discrepancy (lack of heat 

treatment) on a batch of the N°3 and N°4 

hinge sleeves installed on [a] Thrust Reverser 

Unit (TRU) was identified. Those parts are 

only installed on A330 aeroplanes equipped 

with Rolls-Royce (RR) Trent 700 engines. 

This condition, if not corrected, in case of 

a Fan Blade Off event due to high vibration 

level, could cause in-flight loss of some 

heavy components of the TRU, possibly 

resulting in injury to persons on the ground 

[or damage to airplane structure or control 

surfaces, and consequent reduced 

controllability of the airplane]. 

As current hinge sleeves are not serialized, 

it is not possible to identify the TRU hinge 

sleeves which did not receive the heat 

treatment. The part supplier has developed 

an identification procedure for these TRU 

hinge sleeves in order to identify the affected 

hinge sleeves, and to allow a better part 

traceability in the future. 

For the reason described above, this 

[EASA] AD requires identification and 

replacement of the affected TRU hinge 

sleeves. 

You may examine the MCAI in the 

AD docket on the Internet at http:// 

www.regulations.gov/#!documentDetail;

D=FAA-2015-0085-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 7986, February 13, 2015) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data 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 (80 FR 7986, 

February 13, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 7986, 

February 13, 2015). 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A330–78–3021, Revision 03, dated 

October 15, 2014. Aircelle has issued 

Service Bulletin 78–AG924, dated 

September 26, 2012. This service 

information describes procedures for 

modifying and marking the sleeves for 

hinges number 3 and number 4 on the 

cowl doors of Rolls-Royce Trent 700 

engines. 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 of this AD. 


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52936 Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Rules and Regulations 

Costs of Compliance 

We estimate that this AD affects 24 

airplanes of U.S. registry. 

We also estimate that it will take 

about 29 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

about $0 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $59,160, or 

$2,465 per product. 

In addition, we estimate that any 

necessary follow-on action will take up 

to 1 work-hour and require parts costing 

$0, for a cost of $85 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/#!docketDetail;D=

FAA-015-0085; 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 street address for 

the Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

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 adding 

the following new airworthiness 

directive (AD): 

2015–17–22 Airbus: Amendment 39–18255. 

Docket No. FAA–2015–0085; Directorate 

Identifier 2014–NM–078–AD. 

(a) Effective Date 

This AD becomes effective October 7, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus Model A330– 

243, A330–243F, A330–341, A330–342, and 

A330–343 airplanes, certificated in any 

category, all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 78, Exhaust. 

(e) Reason 

This AD was prompted by reports 

indicating that certain hinge sleeves on the 

cowl doors of the thrust reverser units (TRUs) 

were not heat treated. We are issuing this AD 

to prevent, in the event of a fan-blade-off 

event due to high vibration, in-flight loss of 

TRU heavy components, which might 

damage airplane structure or control surfaces 

and consequently reduce controllability of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Identification of TRU Part Number 

Within 12 months after the effective date 

of this AD: Identify the part number of the 

TRUs, in accordance with the information in 

Aircelle Service Bulletin 78–AG924, dated 

September 26, 2012. 

(h) Replacement of TRU Hinge Sleeves 

If the results of the part identification 

required by paragraph (g) of this AD reveal 

that the TRUs are affected: Within the 

compliance time defined in paragraph (g) of 

this AD, replace hinge sleeves numbers 3 and 

4 of each TRU cowl door, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A330–78–3021, Revision 03, 

dated October 15, 2014. 

Note 1 to paragraph (h) of this AD: RollsRoyce Alert Service Bulletin RB.211–78– 

AG924, dated September 26, 2012, is an 

additional source of guidance for replacing 

the TRUs and is not incorporated by 

reference in this AD. 

(i) Optional Terminating Action for 

Paragraphs (g) and (h) of this AD 

Modifying an airplane by incorporating 

Airbus Modification 202463 in production 

terminates the requirements specified in 

paragraphs (g) and (h) of this AD for that 

airplane. 

(j) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install a TRU on any airplane 

unless it has been determined, using Aircelle 

Service Bulletin 78–AG924, dated September 

26, 2012, that the cowl door hinge sleeves 

installed on the TRU are not affected by the 

requirements of this AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (h) of this AD 

if those actions were performed before the 

effective date of this AD using the service 

information identified in paragraphs (k)(1), 

(k)(2), or (k)(3) of this AD, which are not 

incorporated by reference in this AD. 

(1) Airbus Service Bulletin A330–78–3021, 

dated October 17, 2012. 

(2) Airbus Service Bulletin A330–78–3021, 

Revision 01, dated July 30, 2013. 

(3) Airbus Service Bulletin A330–78–3021, 

Revision 02, dated April 17, 2014. 

(l) 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- 


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Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Rules and Regulations 52937 

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: 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) Required for Compliance (RC): Where 

Airbus Service Bulletin A330–78–3021, 

Revision 03, dated October 15, 2014, contains 

procedures or tests that are identified as RC, 

those procedures and tests must be done to 

comply with this AD; any procedures and 

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 operators’ 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 a 

serviceable condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2014–0062, dated March 11, 2014, for related 

information. This MCAI may be found in the 

AD docket on the Internet at http://

www.regulations.gov/#!document

Detail;D=FAA-2015-0085-0002. 

(2) Airbus service information identified in 

this AD that is not incorporated by reference 

is available at the addresses specified in 

paragraphs (n)(3) and (n)(5) of this AD. 

(3) Rolls-Royce service information 

identified in this AD that is not incorporated 

by reference is available at Rolls-Royce plc, 

P.O. Box 31, Derby, DE24 8BJ, England; 

phone: 011–44–1332–242424; fax: 011–244– 

1332–249936; email: http://www.rollsroyce.com/contact/civil_team.jsp; Internet: 

https://www.aeromanager.com. 

(n) 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 A330–78–3021, 

Revision 03, dated October 15, 2014. 

(ii) Aircelle Service Bulletin 78–AG924, 

dated September 26, 2012. 

(3) 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. 

(4) For Aircelle service information 

identified in this AD, contact Aircelle 

Customer support Center, BP 50042, 50, rue 

Pierre Curie, 78371 Plaisir Cedex, France: 

telephone +33 (0)1 64 14 80 33; fax +33 (0)1 

64 14 84 10. 

(5) 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. 

(6) 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 

21, 2015. 

Kevin Hull, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–21475 Filed 9–1–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0680; Directorate 

Identifier 2014–NM–165–AD; Amendment 

39–18236; AD 2015–17–03] 

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 DHC–8–400, 

–401, and –402 airplanes. This AD was 

prompted by a report of a main landing 

gear (MLG) parking brake becoming 

dislodged from its mounting bracket due 

to an improperly installed quick release 

pin of the hand pump lever. This AD 

requires removing the hand pump lever 

of the parking brake from the right-hand 

side nacelle. We are issuing this AD to 

prevent an unsecured lever from 

migrating from its stowed position, 

fouling against the MLG, and 

subsequently puncturing the nacelle 

structure, which could adversely affect 

the safe landing of the airplane. 

DATES: This AD becomes effective 

October 7, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 7, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-0680 or in 

person at the 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. 

For service information identified in 

this AD, contact Bombardier, Inc., QSeries 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. 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– 

0680. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7318; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Bombardier, Inc. Model 

DHC–8–400, -401, and -402 airplanes. 

The NPRM published in the Federal 

Register on April 1, 2015 (80 FR 17366). 

The Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–18, 

dated June 19, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model 

DHC–8–400, –401, and –402 airplanes. 

The MCAI states: 

There has been one (1) reported in-service 

incident where the main landing gear (MLG) 

parking brake hand pump lever was not 

properly secured in the right-hand (RH) side 

nacelle and became dislodged from its 

mounting bracket. During extension of the 

MLG, the unsecured lever shifted causing a 

fouling condition with the nacelle and 

subsequently puncturing the nacelle 

structure. 


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