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. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules 26491 

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 107 airplanes of U.S. registry. 

We also estimate that it would take 

about 4 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 $64 per product. 

Based on these figures, we estimate the 

cost of this proposed AD on U.S. 

operators to be $43,228, or $404 per 

product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. We have 

no way of determining the number of 

aircraft that might need these actions. 

According to the manufacturer, all of 

the costs of this proposed AD may be 

covered under warranty, thereby 

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): 

Bombardier, Inc.: Docket No. FAA–2015– 

0929; Directorate Identifier 2014–NM– 

218–AD. 

(a) Comments Due Date 

We must receive comments by June 22, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

BD–100–1A10 (Challenger 300) airplanes, 

certificated in any category, having serial 

numbers 20003 through 20382 inclusive, 

20384, and 20386. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24, Electrical Power. 

(e) Reason 

This 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. We are issuing 

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; which could adversely 

affect the continued safe operation and 

landing of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection, Repair, and Preventive 

Modification 

Within 36 months after the effective date 

of this AD, do the actions required by 

paragraph (g)(1) and (g)(2) of this AD. 

(1) Do a one-time general visual inspection 

to detect damage (including wear and 

chafing) of the wiring harness, in accordance 

with the Accomplishment Instructions of 

Bombardier, Inc. Service Bulletin 100–24–24, 

dated June 6, 2014. Repair any damage before 

further flight, in accordance with the 

Accomplishment Instructions of Bombardier, 

Inc. Service Bulletin 100–24–24, dated June 

6, 2014; except, where Bombardier, Inc. 

Service Bulletin 100–24–24, dated June 6, 

2014, specifies to contact Bombardier for 

repair instructions, repair using a method 

approved by the Manager, New York Aircraft 

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

or Transport Canada Civil Aviation (TCCA); 

or Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). 

(2) Modify the wiring harness routing in 

accordance with the Accomplishment 

Instructions of Bombardier, Inc. Service 

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

(h) Definition of General Visual Inspection 

For the purposes of this AD, a general 

visual inspection is a visual examination of 

an interior or exterior area, installation, or 

assembly to detect obvious damage, failure, 

or irregularity. This level of inspection is 

made from within touching distance unless 

otherwise specified. A mirror may be 

necessary to ensure visual access to all 

surfaces in the inspection area. This level of 

inspection is made under normally available 

lighting conditions such as daylight, hangar 

lighting, flashlight, or droplight and may 

require removal or opening of access panels 

or doors. Stands, ladders, or platforms may 

be required to gain proximity to the area 

being checked. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York 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 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
26492 Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules 

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, 

FAA; or TCCA; or Bombardier, Inc.’s TCCA 

DAO. If approved by the DAO, the approval 

must include the DAO-authorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–32, dated 

September 8, 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–2015–0929. 

(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 

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 13, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–10947 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–2015–1275; Directorate 

Identifier 2014–NM–070–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2004–14– 

09, for certain Airbus Model A320–211, 

–212, and –231 airplanes. AD 2004–14– 

09 currently requires repetitive 

inspections for fatigue cracking of the 

lower surface panel on the wing center 

box, and repair if necessary; and 

modification of the lower surface panel 

on the wing center box, which 

constitutes terminating action for the 

repetitive inspections. Since we issued 

AD 2004–14–09, we have determined 

that, based on the average flight 

duration, the average weight of fuel at 

landing is higher than that defined for 

the analysis of the fatigue-related tasks; 

and that shot peening might have been 

improperly done on the chromic acid 

anodizing (CAA) protection, which 

would adversely affect fatigue crack 

protection. This proposed AD would 

reduce the compliance times for the 

repetitive inspections, and would 

require a repair for certain airplanes. We 

are proposing this AD to detect and 

correct fatigue cracking of the lower 

surface panel on the wing center box, 

which could result in reduced structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by June 22, 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 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– 

1275; 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–2015–1275; Directorate Identifier 

2014–NM–070–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 

On June 29, 2004, we issued AD 

2004–14–09, Amendment 39–13718 (69 

FR 41398, July 9, 2004). AD 2004–14– 

09 requires actions intended to address 

an unsafe condition on the products 

listed above. AD 2004–14–09 

superseded AD 98–22–05, Amendment 

39–10851 (63 FR 56542, October 22, 

1998). 

Since we issued AD 2004–14–09, 

Amendment 39–13718 (69 FR 41398, 

July 9, 2004), we have determined that, 

based on the average flight duration, the 

average weight of fuel at landing is 

higher than that defined for the analysis 

of the fatigue-related tasks; and that shot 

peening might have been improperly 

done on the CAA protection, which 

would adversely affect fatigue crack 

protection. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0065, dated March 14, 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS