Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules 26487 

(h) Retained Restrictions on Alternative 

Actions, Intervals, and/or CDCCLs, With a 

New Exception 

This paragraph restates the requirements of 

paragraph (k) of AD 2011–21–06, 

Amendment 39–16829 (76 FR 64788, October 

19, 2011), with a new exception. Except as 

required by paragraph (i) of this AD, after 

accomplishing the revision required by 

paragraph (g) of this AD, no alternative 

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

CDCCLs may be used unless the actions, 

intervals, and/or CDCCLs are approved as an 

alternative method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (l) of this AD. 

(i) New Maintenance or Inspection Program 

Revision 

Within 90 days after the effective date of 

this AD: Revise the maintenance or 

inspection program, as applicable, by 

incorporating Subjects 05–10–10, 

‘‘Airworthiness Limitations’’; 05–10–20, 

‘‘Certification Maintenance Requirements’’; 

and 05–10–30, ‘‘Critical Design Configuration 

Control Limitations (CDCCL)—Fuel System’’; 

of Chapter 05, ‘‘Airworthiness Limitations,’’ 

of the BAE Systems (Operations) Limited J41 

AMM, Revision 38, dated September 15, 

2013. The initial compliance times for the 

tasks are at the applicable times specified in 

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

Doing the actions required by this paragraph 

terminates the requirements of paragraph (g) 

of this AD. 

(1) For replacement tasks of life limited 

parts specified in Subject 05–10–10, 

‘‘Airworthiness Limitations,’’ of Chapter 05, 

‘‘Airworthiness Limitations,’’ of the BAE 

Systems (Operations) Limited J41 AMM, 

Revision 38, dated September 15, 2013: Prior 

to the applicable flight cycles (landings) or 

flight hours (flying hours) on the part 

specified in the ‘‘Mandatory Life Limits’’ 

column in Subject 05–10–10, or within 90 

days after the effective date of this AD, 

whichever occurs later. 

(2) For structurally significant item tasks 

specified in Subject 05–10–10, 

‘‘Airworthiness Limitations,’’ of Chapter 05, 

‘‘Airworthiness Limitations,’’ of the BAE 

Systems (Operations) Limited J41 AMM, 

Revision 38, dated September 15, 2013: Prior 

to the accumulation of the applicable flight 

cycles specified in the ‘‘Initial Inspection’’ 

column in Subject 05–10–10, or within 90 

days after the effective date of this AD, 

whichever occurs later. 

(3) For certification maintenance 

requirements tasks specified in Subject 05– 

10–20, ‘‘Certification Maintenance 

Requirements,’’ of Chapter 05, 

‘‘Airworthiness Limitations,’’ of the BAE 

Systems (Operations) Limited J41 AMM, 

Revision 38, dated September 15, 2013: Prior 

to the accumulation of the applicable flight 

hours specified in the ‘‘Time Between 

Checks’’ column in Subject 05–10–20, or 

within 90 days after the effective date of this 

AD, whichever occurs later; except for tasks 

that specify ‘‘first flight of the day’’ in the 

‘‘Time Between Checks’’ column in Subject 

05–10–20, the initial compliance time is the 

first flight of the next day after doing the 

revision required by paragraph (j) of this AD, 

or within 90 days the effective date of this 

AD, whichever occurs later. 

(j) New Restrictions on Alternative Actions, 

Intervals, and/or (CDCCLs) 

After the maintenance or inspection 

program, as applicable, has been revised as 

required by paragraph (i) of this AD, no 

alternative actions (e.g., inspections), 

intervals, and/or CDCCLs may be used unless 

the actions, intervals, and/or CDCCLs are 

approved as an AMOC in accordance with 

the procedures specified in paragraph (l) of 

this AD. 

(k) Credit for Previous Actions 

This paragraph restates the provisions of 

paragraph (j) of AD 2011–21–06, Amendment 

39–16829 (76 FR 64788, October 19, 2011). 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before November 23, 

2011 (the effective date of AD 2011–21–06), 

in accordance with Subjects 05–10–10, 

‘‘Airworthiness Limitations’’; 05–10–20, 

‘‘Certification Maintenance Requirements’’; 

and 05–10–30, ‘‘Critical Design Configuration 

Control Limitations (CDCCL)—Fuel System’’; 

of Chapter 05, ‘‘Airworthiness Limitations,’’ 

of the BAE Systems (Operations) Limited 

Jetstream Series 4100 AMM, Revision 33, 

dated February 15, 2010; which are not 

incorporated by reference in this AD. 

(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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–227–1175; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 

(i) 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. 

(ii) AMOCs approved previously for AD 

2011–21–06, Amendment 39–16829 (76 FR 

64788, October 19, 2011), are not approved 

as AMOCs with this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or BAE Systems (Operations) 

Limited’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0043, dated 

February 21, 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–2015–1279. 

(2) For service information identified in 

this AD, contact BAE SYSTEMS (Operations) 

Limited, Customer Information Department, 

Prestwick International Airport, Ayrshire, 

KA9 2RW, Scotland, United Kingdom; 

telephone +44 1292 675207; fax +44 1292 

675704; email RApublications@

baesystems.com; Internet http://

www.baesystems.com/Businesses/

RegionalAircraft/index.htm. 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 April 29, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–11023 Filed 5–7–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1277; Directorate 

Identifier 2014–NM–155–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 A319, A320, and A321 

series airplanes. This proposed AD was 

prompted by fatigue testing that 

determined fatigue damage could 

appear on clips, shear webs, and angles 

at certain rear fuselage sections and 

certain frames. This proposed AD is 

intended to complete certain mandated 

programs intended to support the 

airplane reaching its limit of validity 

(LOV) of the engineering data that 

support the established structural 

maintenance program. This proposed 

AD would require replacing the clips, 

the shear webs, and angles, including 

doing all applicable related investigative 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
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actions, and repair if necessary. We are 

proposing this AD to prevent fatigue 

damage on the clips, shear webs, and 

angles, which could affect the structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by June 22, 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, 

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 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– 

1277; 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: 

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. 

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–2015–1277; Directorate Identifier 

2014–NM–155–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 

As described in FAA Advisory 

Circular 120-104 (http://www.faa.gov/

documentLibrary/media/Advisory_

Circular/120-104.pdf), several programs 

have been developed to support 

initiatives that will ensure the 

continued airworthiness of aging 

airplane structure. The last element of 

those initiatives is the requirement to 

establish a limit of validity (LOV) of the 

engineering data that support the 

structural maintenance program under 

14 CFR 26.21. This proposed AD is the 

result of an assessment of the previously 

established programs by the DAH 

during the process of establishing the 

LOV for Airbus Model A319, A320, and 

A321 series airplanes. The actions 

specified in this proposed AD are 

necessary to complete certain programs 

to ensure the continued airworthiness of 

aging airplane structure and to support 

an airplane reaching its LOV. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0177, dated July 25, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Airbus 

Model A319, A320, and A321 series 

airplanes. The MCAI states: 

During the A320 fatigue test campaign for 

Extended Service Goal (ESG), it was 

determined that fatigue damage could appear 

on the clips, shear webs and angles at rear 

fuselage section 19, on Frame (FR) 72 and 

FR74. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To address this potential unsafe condition, 

Airbus developed a modification, which has 

been published through Airbus Service 

Bulletin (SB) A320–53–1266 for in-service 

application to allow aeroplanes to operate up 

to the new ESG limit. 

For the reasons described above, this 

[EASA] AD requires replacement of the 

affected clips, shear webs and angles at rear 

fuselage section 19, FR72 and FR74 

[including all applicable related investigative 

actions and repair if any cracking is found]. 

Related investigative actions include 

rotating probe testing for cracking of the 

fastener holes and high frequency eddy 

current inspections for cracking of the 

stringers. 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– 

1277. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–53–1266, Revision 01, dated June 

20, 2013. This service information 

describes procedures for replacing clips, 

shear webs, and angles at rear fuselage 

section 19, FR72 and FR74. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 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 NPRM. 

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 these same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 44 airplanes of U.S. registry. 

We also estimate that it would take 

about 110 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $411,400, or $9,350 per product. 

We have received no definitive data 

on the costs of required parts. 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 


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Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules 26489 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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. 

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–2015–1277; 

Directorate Identifier 2014–NM–155–AD. 

(a) Comments Due Date 

We must receive comments by June 22, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

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

AD, certificated in any category, all 

manufacturer serial numbers, except those on 

which Airbus Modification 30975 has been 

embodied in production. 

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

–114, –115, –131, –132, and –133 airplanes. 

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

–231, –232, and –233 airplanes. 

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

–211, –212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by fatigue testing 

that determined fatigue damage could appear 

on clips, shear webs, and angles at certain 

rear fuselage sections and certain frames. 

This AD is intended to complete certain 

mandated programs intended to support the 

airplane reaching its limit of validity (LOV) 

of the engineering data that support the 

established structural maintenance program. 

We are issuing this AD to prevent fatigue 

damage on the clips, shear webs, and angles, 

which could affect the structural integrity of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement 

At the later of the times specified in 

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

Replace the clips, shear webs, and angles at 

rear fuselage section 19, frame (FR)72 and 

FR74, and do all applicable related 

investigative actions before further flight, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1266, Revision 01, dated June 20, 2013. 

If any crack is found during any related 

investigative action required by this AD: 

Before further flight, repair 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). 

(1) Before exceeding 48,000 flight cycles or 

96,000 flight hours, whichever occurs first 

since the airplane’s first flight. 

(2) Within 30 days after the effective date 

of this AD. 

(h) Additional Replacement for Airplanes on 

Which the Replacement Required by 

Paragraph (g) of This AD Is Done Before 

30,000 Flight Cycles or 60,000 Flight Hours 

For airplanes on which the replacement of 

clips, shear webs, and angles specified in 

Airbus Service Bulletin A320–53–1266 is 

done before accumulating 30,000 flight 

cycles or 60,000 flight hours, whichever 

occurred first since the airplane’s first flight: 

Within 30,000 flight cycles or 60,000 flight 

hours, whichever occurs first after that 

replacement, do the replacement specified in 

paragraph (g) of this AD. 

(i) Credit for Previous Actions 

Except as required by paragraph (h) of this 

AD: This paragraph provides credit for the 

replacement required by paragraph (g) of this 

AD, if those actions were performed before 

the effective date of this AD using Airbus 

Service Bulletin A320–53–1266, dated 

January 11, 2013, which is not incorporated 

by reference in this AD. 

(j) 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: 

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 EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0177, dated 

July 25, 2014, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov by 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
26490 Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules 

searching for and locating Docket No. FAA– 

2015–1277. 

(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 April 29, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–10948 Filed 5–7–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0929; Directorate 

Identifier 2014–NM–218–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 BD–100–1A10 

(Challenger 300) airplanes. This 

proposed AD was prompted by multiple 

reports of chafing found on an electrical 

wiring harness in the aft equipment bay, 

caused by contact between the wiring 

harness and a neighboring hydraulic 

line. This proposed AD would require 

an inspection, repair if necessary, and 

modification of the wiring harness 

installation to ensure that the wiring 

harness routing is correct and a 

minimum clearance between the wire 

and the hydraulic line is maintained. 

We are proposing this AD to detect and 

correct chafing on an electrical wiring 

harness, which could cause an electrical 

short circuit or lead to a malfunction of 

the flight control system, the engine 

indication system, or the hydraulic 

power control system, and adversely 

affect the continued safe operation and 

landing of the airplane. 

DATES: We must receive comments on 

this proposed AD by June 22, 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 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 by searching for 

and locating Docket No. FAA–2015– 

0929; 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: 

Assata Dessaline, Aerospace Engineer, 

Avionics and Service Branch, ANE–172, 

FAA, New York Aircraft Certification 

Office, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone: 516– 

228–7301; fax: 516–794–5531. 

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–2015–0929; Directorate Identifier 

2014–NM–218–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–2014–32, 

dated September 8, 2014 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model BD– 

100–1A10 (Challenger 300) airplanes. 

The MCAI states: 

There have been multiple in-service 

reports of chafing found on an electrical 

wiring harness in the aft equipment bay. An 

investigation determined that the chafing was 

attributed to contact between the wiring 

harness and a neighboring hydraulic line. 

This chafing could cause an electrical short 

circuit or lead to a malfunction of the flight 

control system, the engine indication system, 

or the hydraulic power control system; which 

could adversely affect the continued safe 

operation and landing of the aeroplane. 

This [Canadian] AD mandates the 

inspection [general visual inspection], 

rectification as required [repair of damage 

(including wear and chafing)], and 

modification of the wiring harness 

installation to ensure the correct wiring 

routing and a minimum clearance between 

the wire and the hydraulic line is 

maintained. 

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– 

0929. 

Related Service Information Under 1 

CFR Part 51 

Bombardier, Inc. has issued Service 

Bulletin 100–24–24, dated June 6, 2014. 

The service information describes 

procedures for an inspection, repair if 

necessary, and modification to reroute 

wiring harness installation to prevent 

contact with the hydraulic line. 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 NPRM. 


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