3522 Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules 

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

all manufacturer serial numbers on which 

Airbus modification (mod) 160500 or mod 

160023 has been embodied in production, 

and those that have been modified in service 

through the Airbus Service Bulletin A320– 

57–1173, A320–57–1186, and A320–57–1187 

except those on which Airbus mod 156108 

has been embodied in production. 

(1) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(2) Model A320–211, –212, –214, –231, 

–232, and –233 airplanes. 

(3) Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by reports that on 

airplanes equipped with sharklets, discretes 

(used to activate the load alleviation 

function) are connected on various flight 

computers using the same ground point. In 

these cases, the ground point segregation is 

no longer effective and a single failure could 

lead to loss of sharklet identification by flight 

computers causing a return to the wing tip 

fence (no sharklet configuration) 

performance. We are issuing this AD to 

prevent loss of sharklet identification by the 

flight computers and subsequent reduced 

control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

Within 24 months after the effective date 

of this AD, modify the sharklet ground 

connection, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–27–1240, dated June 

18, 2014. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM 116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; 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: 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. 

(i) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2014–0186, dated August 19, 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–2014–1051. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office–EIAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@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 

13, 2015. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–00945 Filed 1–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–1049; Directorate 

Identifier 2013–NM–110–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc., 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 

Bombardier, Inc. Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. This proposed AD was 

prompted by reports of the horizontal 

stabilizer trim actuator (HSTA) spur 

gear bolts inside the gearbox found 

loose, broken, or backed out due to 

incorrect bending of the anti-rotation tab 

washer and the improper application of 

glue during installation. This proposed 

AD would require replacing certain 

HSTAs with a new HSTA. This 

proposed AD would also require 

revising the airplane flight manual 

(AFM) and the maintenance or 

inspection program, as applicable. We 

are proposing this AD to prevent failure 

of the HSTA and subsequent loss of 

control of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 9, 2015. 

ADDRESSES: You may send comments 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 Bombardier, 

Inc., 400 Coˆte-Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone 

514–855–5000; fax 514–855–7401; email 

thd.crj@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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; 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 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: 

Luke Walker, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE– 

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone 516–228–7363; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules 3523 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–1049; Directorate Identifier 

2013–NM–110–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 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2013–14, 

dated June 4, 2013 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model CL– 

600–2B19 (Regional Jet Series 100 & 

440) airplanes. The MCAI states: 

There have been a number of reports where 

the HSTA spur gear bolts inside the gearbox 

were found loose, broken or backed out. 

Investigation revealed that the root cause is 

incorrect bending of the anti-rotation tab 

washer and the improper application of 

Loctite glue during installation. 

The function of these bolts is to generate 

sufficient preload between the two spur gears 

such that the full torque is transferred by 

friction between the two spur gears. 

Loosening of the bolts would reduce the preload between two spur gears and decrease the 

torque transfer. Partial or full torque would 

be re-distributed to the secondary load path 

(Tie-Rod) in torsion. The Tie-Rod is designed 

to withstand axial load only in case of failure 

of the primary load path (ACME screw), and 

not torsional load. The secondary load path 

(Tie-Rod) is therefore considered ineffective 

and no longer provides protection as a 

failsafe design of the system. Loose bolt(s) on 

the HSTA spur gear combined with the 

failure of the primary load path, could lead 

to failure of the HSTA and subsequent loss 

of the aeroplane. 

In addition, Bombardier Aerospace (BA) 

has introduced a modified HSTA [part 

number] P/N 601R92305–5 (vendor P/N 

8396–4) to rectify the loose bolt problem. 

However, this modified HSTA, has several 

quality control problems which could affect 

safety. 

This [Canadian] AD is issued to mandate 

the replacement of the affected HSTA(s) with 

the new HSTA P/N 601R92305–7 (vendor P/ 

N 8396–5). 

This proposed AD also would require 

revising the AFM and maintenance or 

inspection program, 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–2014– 

1049. 

Related Service Information 

Bombardier has issued the following 

service information. 

• Bombardier Service Bulletin 601R– 

27–161, Revision A, dated January 30, 

2014. This service information describes 

procedures for installing an HSTA. 

• Bombardier CL–600–2B19, 

Temporary Revision 2A–56, dated June 

4, 2012, to Appendix A, Certification 

Maintenance Requirements (CMR), of 

Part 2, Airworthiness Requirements, of 

the Bombardier CL–600–2B19 

Maintenance Requirements Manual 

(MRM). This service information adds 

new CMR tasks to the Airworthiness 

Requirements of the MRM. These CMR 

tasks include an inspection, functional 

check, and operational check. 

• Bombardier Model CL–600–2B19 

Airplane Flight Manual, CSP A–012, 

Volume 3, Revision 61, dated April 2, 

2013. This service information revises 

the Limitations section of the AFM to 

include a horizontal stabilizer trim 

check before the first flight of the day. 

In addition, this service information 

revises the Normal Procedures section 

of the AFM to include details for the 

horizontal stabilizer trim check portion 

of the procedure. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

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. 

Costs of Compliance 

We estimate that this proposed AD 

affects 85 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

HSTA replacement ................. 8 work-hours × $85 per hour = $680 ..................................... $38,569 $39,249 $3,336,165 

Revise airplane flight manual 1 work-hour × $85 per hour = $85 ......................................... 0 85 7,225 

Revise maintenance or inspection program.1 work-hour × $85 per hour = $85 ......................................... 0 85 7,225 

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 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. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
3524 Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules 

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): 

Bombardier, Inc.: Docket No. FAA–2014– 

1049; Directorate Identifier 2013–NM– 

110–AD. 

(a) Comments Due Date 

We must receive comments by March 9, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2B19 (Regional Jet Series 100 & 440) 

airplanes, certificated in any category, serial 

numbers 7003 and subsequent, equipped 

with horizontal stabilizer trim actuator 

(HSTA) part number (P/N) 601R92305–1 

(vendor P/N 8396–2), 601R92305–3 (vendor 

P/N 8396–3), or 601R92305–5 (vendor P/N 

8396–4). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by reports of the 

HSTA spur gear bolts inside the gearbox 

found loose, broken, or backed out due to 

incorrect bending of the anti-rotation tab 

washer and the improper application of 

Loctite glue during installation. We are 

issuing this AD to prevent failure of the 

HSTA and subsequent loss of control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Airplane Flight Manual (AFM) Revision 

Within 30 days after the effective date of 

this AD, revise the Limitations section and 

Normal Procedures section of the AFM to 

include the information in Supplement 23, 

‘‘Horizontal Stabilizer Trim Check,’’ of 

Chapter 7 ‘‘Supplements,’’ of Bombardier 

CL–600–2B19 Airplane Flight Manual CSP 

A–012, Volume 3, Revision 61, dated April 

2, 2013. 

(h) Maintenance/Inspection Program 

Revision 

Within 30 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate Task 

C27–40–103–04, ‘‘Operational Check (ground 

maintenance test) of the horizontal stabilizer 

trim control unit,’’ specified in Bombardier 

CL–600–2B19 Temporary Revision 2A–56, 

dated June 4, 2012, to Appendix A, 

Certification Maintenance Requirements, of 

Part 2, Airworthiness Requirements, of the 

Bombardier CL–600–2B19 Maintenance 

Requirements Manual (MRM). The 

compliance time for the initial operational 

check is within 500 flight hours after the 

effective date of this AD. 

(i) No Alternative Actions or Intervals 

After accomplishing the revision required 

by paragraph (h) of this AD, no alternative 

actions (e.g., inspections) and/or intervals 

may be used unless the actions and/or 

intervals are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (m) of this AD. 

(j) HSTA Replacement 

(1) For airplanes equipped with an HSTA 

having P/N 601R92305–1 (vendor P/N 8396– 

2) or P/N 601R92305–3 (vendor P/N 8396–3): 

At the earlier of the times specified in 

paragraphs (j)(1)(i) and (j)(1)(ii) of this AD, 

replace the HSTA with a new HSTA having 

P/N 601R92305–7 (vendor P/N 8396–5), in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–27–161, Revision A, dated January 30, 

2014. The compliance times specified in 

paragraphs (j)(1)(i) and (j)(1)(ii) of this AD do 

not alleviate any existing life limit 

requirements. 

(i) Within 3,700 flight hours after the 

effective date of this AD. 

(ii) Within 27 months after the effective 

date of this AD. 

(2) For airplanes equipped with an HSTA 

having P/N 601R92305–5 (vendor P/N 8396– 

4): At the earlier of the times specified in 

paragraphs (j)(2)(i), (j)(2)(ii), and (j)(2)(iii) of 

this AD, replace the HSTA with a new HSTA 

having P/N 601R92305–7 (vendor P/N 8396– 

5), in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–27–161, Revision A, dated January 30, 

2014. The compliance times specified in 

paragraphs (j)(2)(i), (j)(2)(ii), and (j)(2)(iii) of 

this AD do not alleviate any existing life limit 

requirements. 

(i) Within 4,400 flight hours after the 

effective date of this AD. 

(ii) Within 32 months after the effective 

date of this AD. 

(iii) Before the accumulation of 10,000 total 

flight hours on HSTA P/N 60192305–5 

(vendor P/N 8396–4). 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (j) of this AD, 

if those actions were performed before the 

effective date of this AD using Bombardier 

Service Bulletin 601R–27–161, dated May 31, 

2012, which is not incorporated by reference 

in this AD. 

(l) Parts Installation Limitations 

(1) As of the effective date of this AD, no 

person may install an HSTA, P/N 

601R92305–1 (vendor P/N 8396–2) or P/N 

601R92305–3 (vendor P/N 8396–3) on any 

Model CL–600–2B19 airplane. 

(2) As of the effective date of this AD, no 

person may install an HSTA, P/N 

601R92305–5 (vendor P/N 8396–4) having 

serial number (S/N) 287, 724, 813, 841, 998, 

1031, 1035, 1049, 1053, 1067, 1068, 1136, 

1252, 1268, 1303, 1319, 1338, 1354, 1374, 

1378, 1445, 1470, 1498, 1513, 1546, 1632, 

1736, 1766, 1846, 1849, 2002 through 2009 

inclusive, 2011, 2013 through 2016 inclusive, 

2019, 2020, or 2022, on any Model CL–600– 

2B19 airplane. 

(3) As of the effective date of this AD: 

Replacement of an HSTA, P/N 601R92305–1 

(vendor P/N 8396–2), P/N 601R92305–3 

(vendor P/N 8396–3), or P/N 601R92305–5 

(vendor P/N 8396–4), with an HSTA having 

P/N 601R92305–5 (vendor P/N 8396–4) that 

is not identified in paragraph (l)(2) of this 

AD, is acceptable, provided the actions 

required by paragraph (j)(2) of this AD are 

accomplished within the compliance time 

specified in that paragraph. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. 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, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

Transport Canada Civil Aviation (TCCA); or 


emcdonald on DSK67QTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules 3525 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–14, dated 

June 4, 2013, 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– 

2014–1049. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

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. 

Issued in Renton, Washington, on January 

13, 2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–00958 Filed 1–22–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–1045; Directorate 

Identifier 2014–NM–031–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 A310 and Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

series airplanes, and Model A300 C4– 

605R Variant F airplanes (collectively 

called Model A300–600 series airplanes) 

series airplanes. This proposed AD was 

prompted by a report of skin disbonding 

and damage found on the composite 

side panel of the rudder, located 

between the rudder core and skin of a 

previously repaired area. This proposed 

AD would require an inspection for 

disbonding or damage of certain 

rudders, and related investigative 

actions and corrective actions if 

necessary. We are proposing this AD to 

detect and correct disbonding and 

damage of the rudder, which could 

result in reduced structural integrity of 

the rudder and consequent reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 9, 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—EAW, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@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–2014– 

1045; 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

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–2014–1045; Directorate Identifier 

2014–NM–031–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 2014–0026, dated January 28, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for the specified 

products. The MCAI states: 

A case of skin disbonding was reported on 

a composite side of a rudder installed on an 

A310 aeroplane. 

The investigation results revealed that this 

disbonding started from a skin panel area 

previously repaired in-service in accordance 

with the Structural Repair Manual (SRM). 

The initial damage has been identified as 

a disbonding between the core and the 

repaired area. This damage may not be 

visually detectable and likely propagates 

during normal operation due to the variation 

of pressure during ground-air-ground cycles. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the rudder, possibly resulting in reduced 

control of the aeroplane. 

For the reasons described above, this 

[EASA] AD requires a one-time 

thermography inspection of each repaired 

rudder or rudder whose maintenance records 

are incomplete and, depending on findings, 

accomplishment of applicable corrective and 

follow-up actions. 

Related investigative actions include 

doing a pulse thermography inspection 

for disbonding or damage of the leftand right-hand rudder side shells; a core 

ventilation through the inner skin, an 

elasticity laminate checker or ultrasonic 

inspection around the identified repairs 

in the booster area, and around 

identified fluid ingress; and a Tap test 

inspection of the glass fiber reinforced 

plastic area to identify skin-to-core 

disbonding and on identified repairs. 


emcdonald on DSK67QTVN1PROD with PROPOSALS