7986 Federal Register / Vol. 80, No. 30 / Friday, February 13, 2015 / Proposed Rules 

12On Dec. 18, 2014, the OCC issued an interim 

final rule with request for comment (IFR) amending 

12 CFR 5.47. 79 FR 75417. The effective date of the 

IFR was Jan. 1, 2015. In an effort to provide the 

fullest opportunity for public comment, the OCC 

invites comment on the IFR through both the 

process outlined in the IFR and the EGRPRA 

Review Process outlined above. 

Dated: January 20, 2015. 

Thomas J. Curry, 

Comptroller of the Currency. 

By order of the Board of Governors of the 

Federal Reserve System, February 6, 2015. 

Robert DeV. Frierson, 

Secretary of the Board. 

Dated: January 21, 2015. 

By order of the Board of Directors. 

Federal Deposit Insurance Corporation. 

Robert E. Feldman, 

Executive Secretary. 

[FR Doc. 2015–02998 Filed 2–12–15; 8:45 am] 

BILLING CODE 4810–33–P; 6510–01–P; 6714–01–C 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0085; Directorate 

Identifier 2014–NM–078–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Model A330–243, A330–243F, 

A330–341, A330–342, and A330–343 

airplanes. This proposed 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 proposed AD 

would require replacing the sleeves of 

certain hinges on the cowl doors of the 

TRUs with new parts. We are proposing 

this AD to prevent, in the event of a fanblade-off event due to high vibration, inflight loss of TRU heavy components, 

which might damage airplane structure 

or control surfaces, and consequent 

reduced controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 30, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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. 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. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALSEP13FE15.002</GPH>
Federal Register / Vol. 80, No. 30 / Friday, February 13, 2015 / Proposed Rules 7987 

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– 

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 proposed 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. Comments will 

be available in the AD docket shortly 

after receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–0085; Directorate Identifier 

2014–NM–078–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

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 by searching for 

and locating Docket No. FAA–2015– 

0085. 

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. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. This service information is 

reasonably available; see ADDRESSES for 

ways to access this service information. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Explanation of ‘‘RC’’ Procedures and 

Tests in Service Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directives Implementation Aviation 

Rulemaking Committee (AD ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which procedures and tests 

in the service information are required 

for compliance with an AD. 

Differentiating these procedures and 

tests from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The actions specified in 

Airbus Service Bulletin A330–78–3021, 

Revision 03, dated October 15, 2014, 

include procedures and tests that are 

identified as RC (required for 

compliance) because these procedures 

have a direct effect on detecting, 

preventing, resolving, or eliminating an 

identified unsafe condition. 

As specified in a NOTE under the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–78–3021, 

Revision 03, dated October 15, 2014, 

procedures and tests identified as RC 

must be done to comply with the 

proposed AD. However, 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 alternative method of compliance 

(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 will require approval of 

an AMOC. 

Costs of Compliance 

We estimate that this proposed AD 

affects 24 airplanes of U.S. registry. 

We also estimate that it would take 

about 29 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $0 per product. 

Based on these figures, we estimate the 

cost of this proposed AD on U.S. 

operators to be $59,160, or $2,465 per 

product. 

In addition, we estimate that any 

necessary follow-on action would 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. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
7988 Federal Register / Vol. 80, No. 30 / Friday, February 13, 2015 / Proposed Rules 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Airbus: Docket No. FAA–2015–0085; 

Directorate Identifier 2014–NM–078–AD. 

(a) Comments Due Date 

We must receive comments by March 30, 

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 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 thrust 

reverser unit (TRU) heavy components, 

which might damage airplane structure or 

control surfaces, and consequent reduced 

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 Aircelle Service 

Bulletin 78–AG924, dated September 26, 

2012. 

(h) Replacement of Thrust Reverser Unit 

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. 

(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 Limitations 

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 (j)(1), 

(j)(2), or (j)(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– 

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) 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. 

(3) 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. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 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 by 

searching for and locating Docket No. FAA– 

2015–0085. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 30 / Friday, February 13, 2015 / Proposed Rules 7989 

(2) 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. 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. 

Issued in Renton, Washington, on January 

30, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–02537 Filed 2–12–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0083; Directorate 

Identifier 2014–NM–131–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A330–200, A330–200 

Freighter, and A330–300 series 

airplanes; and all A340–200 and A340– 

300 series airplanes. This proposed AD 

was prompted by reports that a bracket 

that attaches the cockpit instrument 

panel to the airplane structure, does not 

sustain the fatigue loads of the design 

service goal. This proposed AD would 

require repetitive inspections of that 

bracket for cracking and to determine if 

both lugs are fully broken, an inspection 

for cracking of an adjacent bracket, if 

necessary, and corrective actions if 

necessary. This AD would also provide 

an optional modification, which would 

terminate the repetitive inspections. We 

are proposing this AD to detect and 

correct cracking on a bracket of the 

cockpit instrument panel, which, 

combined with failure of the horizontal 

beam, could lead to collapse of the 

cockpit panel, and reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 30, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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. 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. 

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– 

0083; 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 proposed 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. Comments will 

be available in the AD docket shortly 

after receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–0083; Directorate Identifier 

2014–NM–131–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0127, dated May 15, 

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, A330–200 Freighter, 

and A330–300 series airplanes; and all 

A340–200, and A340–300 series 

airplanes. The MCAI states: 

During flight tests, high stress levels have 

been measured on the bracket No 6 which 

attaches the cockpit instrument panel to the 

aeroplane structure, apparently introduced 

through the nose landing gear due to bumps 

on the runway. Airbus determined that the 

bracket does not sustain the fatigue loads 

during the Design Service Goal (DSG). This 

condition, if not detected and corrected, 

combined with failure of the horizontal 

beam, could lead to collapse of the cockpit 

panel, possibly resulting in reduced control 

of the aeroplane. 

To address this potential unsafe condition, 

Airbus developed a program to inspect the 

condition of the affected cockpit instrument 

panel bracket No 6, and designed a stronger 

(reinforced titanium undrilled) bracket. The 

new bracket can be installed in-service 

through Airbus Service Bulletin (SB) A330– 

25–3548 or SB A340–25–4354, as applicable 

to aeroplane type. 

For the reasons described above, this 

[EASA] AD requires repetitive inspections of 

the cockpit instrument panel bracket No 6 

and, depending on findings, the 

accomplishment of applicable corrective 

actions. This [EASA] AD also provides the 

installation of the stronger bracket as 

optional terminating action for the repetitive 

actions required by this [EASA] AD. 

The corrective actions include replacing 

bracket No. 6 and bracket No. 7 with 

serviceable parts, and repair, as 

applicable. 

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– 

0083. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS