Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules 63141 

TABLE 1 TO PARAGRAPH (i) OF THIS

AD—REPLACEMENT COMPLIANCE

TIMES—Continued 

Year of 

manufacture Compliance time 

2009 .................. Before exceeding 10 years 

since date of manufacture of the passenger 

chemical oxygen generator. 

(j) Definition of Serviceable 

For the purpose of this AD, a serviceable 

unit is a passenger chemical oxygen 

generator having P/N 117042–XX with a 

manufacturing date not older than 10 years, 

or any other approved part number, provided 

that the generator has not exceeded the life 

limit established for that generator by the 

manufacturer. 

(k) Reporting 

At the applicable time specified in 

paragraph (k)(1) or (k)(2) of this AD, submit 

a report of the findings (both positive and 

negative) of the inspection required by 

paragraph (g) of this AD, in accordance with 

paragraph 7., ‘‘Reporting,’’ of Airbus AOT 

A35N006–14, dated December 10, 2014, 

including Appendix 01. The report must 

include the information specified in 

Appendix 1 of Airbus AOT A35N006–14, 

dated December 10, 2014. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(l) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install a passenger chemical 

oxygen generator, unless it is determined, 

prior to installation, that the oxygen 

generator is a serviceable unit as specified in 

paragraph (j) of this AD. 

(m) 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 European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with, a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive EASA AD 2015– 

0117, dated June 24, 2015; corrected August 

7, 2015, 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– 

2015–3989. 

(2) For Airbus 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. For BE service 

identified in this proposed AD, contact B/E 

Aerospace Inc., 10800 Pflumm Road, Lenexa, 

KS 66215; telephone: 913–338–9800; fax: 

913–469–8419; Internet http://

beaerospace.com/home/globalsupport. 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 October 

6, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–26220 Filed 10–16–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3988; Directorate 

Identifier 2015–NM–005–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 supersede 

Airworthiness Directive (AD) 2014–17– 

51, for certain Bombardier, Inc. Model 

CL–600–2B16 airplanes. AD 2014–17– 

51 currently requires inspecting the 

inboard flap fasteners of the hinge-box 

forward fitting at Wing Station (WS) 

76.50 and WS 127.25 to determine the 

orientation and condition of the 

fasteners, as applicable, and 

replacement or repetitive inspections of 

the fasteners if necessary. AD 2014–17– 

51 also provides for optional 

terminating action for the requirements 

of that AD. Since we issued AD 2014– 

17–51, we have determined that 

additional action is necessary. This 

proposed AD would also require 

accomplishment of the previously 

optional terminating action. We are 

proposing this AD to detect and correct 

incorrectly oriented or fractured 

fasteners, which could result in 

premature failure of the fasteners 

attaching the inboard flap hinge-box 

forward fitting; failure of the fasteners 

could lead to the detachment of the flap 

hinge box and the flap surface, and 

consequent loss of control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by December 3, 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. 


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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– 

3988; 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: Aziz 

Ahmed, Aerospace Engineer, Propulsion 

and Services Branch, ANE–173, FAA, 

New York Aircraft Certification Office 

(ACO), 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone 516– 

228–7329; 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–2015–3988; Directorate Identifier 

2015–NM–005–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 October 13, 2014, we issued AD 

2014–17–51, Amendment 39–17999 (79 

FR 64088, October 28, 2014). AD 2014– 

17–51 requires actions intended to 

address an unsafe condition on certain 

Bombardier, Inc. Model CL–600–2B16 

airplanes. 

The preamble to AD 2014–17–51, 

Amendment 39–17999 (79 FR 64088, 

October 28, 2014), explains that we 

consider the requirements ‘‘interim 

action’’ and were considering further 

rulemaking. We now have determined 

that further rulemaking is indeed 

necessary, and this proposed AD 

follows from that determination. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–27R1, 

dated August 29, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model CL– 

600–2B16 airplanes. The MCAI states: 

There have been three in-service reports on 

604 Variant aeroplanes of a fractured fastener 

head on the inboard flap hinge-box forward 

fitting at Wing Station (WS) 76.50, found 

during a routine maintenance inspection. 

Investigation revealed that the installation of 

these fasteners on the inboard flap hinge-box 

forward fittings at WS 76.50 and WS 127.25, 

on both wings, does not conform to the 

engineering drawings. Incorrect installation 

may result in premature failure of the 

fasteners attaching the inboard flap hinge-box 

forward fitting. Failure of the fasteners could 

lead to the detachment of the flap hinge box 

and consequently the detachment of the flap 

surface. The loss of a flap surface could 

adversely affect the continued safe operation 

of the aeroplane. 

The original issue of [Canadian] AD CF– 

2013–39 [http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0054-0002] 

[which corresponds to FAA AD 2014–03–17, 

Amendment 39–17754 (79 FR 9389, February 

19, 2014)] mandated a detailed visual 

inspection (DVI) of each inboard flap hingebox forward fitting, on both wings, and 

rectification as required. Incorrectly oriented 

fasteners require repetitive inspections until 

the terminating action is accomplished. 

After the issuance of [Canadian] AD CF– 

2013–39, there has been one reported 

incident on a 604 Variant aeroplane where 

four fasteners were found fractured on the 

same flap hinge-box forward fitting. The 

investigation determined that the fasteners 

were incorrectly installed. 

The original issue of this [Canadian] AD 

was issued to reduce the initial and repetitive 

inspection intervals previously mandated in 

[Canadian] AD CF–2013–39, and to impose 

replacement of the incorrectly oriented 

fasteners within 24 months. The CL–600– 

1A11, –2A12 and –2B16 (601–3A/–3R 

Variant) aeroplanes are addressed through 

[Canadian] AD CF–2013–39R1. 

Revision 1 of this [Canadian] AD is issued 

to clarify the requirements for the initial and 

repetitive inspections. 

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– 

3988. 

Related Service Information Under 1 

CFR Part 51 

Bombardier has issued Alert Service 

Bulletins: 

• A604–57–006, Revision 04, dated 

November 12, 2014, including 

Appendices 1 and 2, dated September 

26, 2013, 

• A605–57–004, Revision 04, dated 

November 12, 2014, including 

Appendices 1 and 2, dated September 

26, 2013, and 

The service information describes 

detailed visual inspection of each 

inboard flap fastener of the hinge-box 

forward fitting at WS 76.50 and WS 

127.25, on both wings, and, if necessary, 

replacement of the fasteners. 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 the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

affects 285 airplanes of U.S. registry. 

The actions required by AD 2014–17– 

51, Amendment 39–17999 (79 FR 

64088, October 28, 2014), and retained 

in this proposed AD take about 1 workhour per product, at an average labor 

rate of $85 per work-hour. Required 

parts cost about $0 per product. Based 

on these figures, the estimated cost of 

the actions that are required by AD 

2014–17–51 is $85 per product. 

We also estimate that it would take 

about 58 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 $753 per 

product. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $1,619,655, or 

$5,683 per product. 


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In addition, we estimate that any 

necessary follow-on actions would take 

about 58 work-hours and require parts 

costing $753, for a cost of $5,683 per 

product. We have no way of 

determining the number of aircraft that 

might need this action. 

According to the manufacturer, some 

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 

removing Airworthiness Directive (AD) 

2014–17–51, Amendment 39–17999 (79 

FR 64088, October 28, 2014), and 

adding the following new AD: 

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

3988; Directorate Identifier 2015–NM– 

005–AD. 

(a) Comments Due Date 

We must receive comments by December 3, 

2015. 

(b) Affected ADs 

(1) This AD replaces AD 2014–17–51, 

Amendment 39–17999 (79 FR 64088, October 

28, 2014). 

(2) This AD affects AD 2014–03–17, 

Amendment 39–17754 (79 FR 9389, February 

19, 2014), only for the airplanes identified in 

paragraph (c) of this AD. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2B16 airplanes, certificated in any 

category, serial numbers 5301 through 5665 

inclusive, and 5701 through 5920 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports of 

fractured fastener heads on the inboard flap 

hinge-box forward fitting at Wing Station 

(WS) 76.50 due to incorrect installation. We 

are issuing this AD to detect and correct 

incorrectly oriented or fractured fasteners, 

which could result in premature failure of 

the fasteners attaching the inboard flap 

hinge-box forward fitting; failure of the 

fasteners could lead to the detachment of the 

flap hinge box and the flap surface, and 

consequent loss of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection, With New Service 

Information: Airplanes Not Previously 

Inspected 

This paragraph restates the requirements of 

paragraph (g) of AD 2014–17–51, 

Amendment 39–17999 (79 FR 64088, October 

28, 2014), with new service information. For 

airplanes on which the actions required by 

AD 2014–03–17, Amendment 39–17754 (79 

FR 9389, February 19, 2014), have not been 

done as of November 12, 2014 (the effective 

date of AD 2014–17–51): Within 10 flight 

cycles after November 12, 2014, or within 

100 flight cycles after March 6, 2014 (the 

effective date of AD 2014–03–17, 

Amendment 39–17754 (79 FR 9389, February 

19, 2014)), whichever occurs first, do a 

detailed visual inspection of each inboard 

flap fastener of the hinge-box forward fitting 

at WS 76.50 and WS 127.25, on both wings, 

to determine if the fasteners are correctly 

oriented and intact (non-fractured, with 

intact fastener head). Do the inspection in 

accordance with the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin A604–57–006, Revision 01, dated 

September 26, 2013, including Appendices 1 

and 2, dated September 26, 2013, Revision 

02, dated January 22, 2014, including 

Appendices 1 and 2, dated September 26, 

2013, or Revision 04, dated November 12, 

2014, including Appendices 1 and 2, dated 

September 26, 2013 (for serial numbers 5301 

through 5665 inclusive); or Bombardier Alert 

Service Bulletin A605–57–004, Revision 01, 

dated September 26, 2013, including 

Appendices 1 and 2, dated September 26, 

2013, Revision 02, dated January 22, 2014, 

including Appendices 1 and 2, dated 

September 26, 2013, or Revision 04, dated 

November 12, 2014, including Appendices 1 

and 2, dated September 26, 2013 (for serial 

numbers 5701 through 5920 inclusive). As of 

the effective date of this AD, only use 

Bombardier Alert Service Bulletin A604–57– 

006, Revision 04, dated November 12, 2014, 

including Appendices 1 and 2, dated 

September 26, 2013; or Bombardier Alert 

Service Bulletin A605–57–004, Revision 04, 

dated November 12, 2014, including 

Appendices 1 and 2, dated September 26, 

2013; as applicable; for the actions required 

by this paragraph. 

(1) If all fasteners are found intact and 

correctly oriented, no further action is 

required by this AD. 

(2) If any fastener is found fractured: Before 

further flight, remove and replace all forward 

and aft fasteners at WS 76.50 and WS 127.25, 

regardless of condition or orientation, on 

both wings, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraph (g) of this AD. As of the effective 

date of this AD, only use Bombardier Alert 

Service Bulletin A604–57–006, Revision 04, 

dated November 12, 2014, including 

Appendices 1 and 2, dated September 26, 

2013; or Bombardier Alert Service Bulletin 

A605–57–004, Revision 04, dated November 

12, 2014, including Appendices 1 and 2, 

dated September 26, 2013; as applicable; for 

the actions required by this paragraph. After 

replacement of all fasteners as required by 

this paragraph of this AD, no further action 

is required by this AD. 


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(3) If any incorrectly oriented but intact 

fastener is found, and no fractured fastener 

is found, repeat the inspection required by 

paragraph (g) of this AD thereafter at 

intervals not to exceed 10 flight cycles, until 

the requirements of paragraph (i)(1) or (k) of 

this AD have been done. 

(h) Retained Actions, With New Service 

Information: Airplanes Previously 

Inspected, Having Incorrectly Oriented 

Fastener(s) 

This paragraph restates the requirements of 

paragraph (h) of AD 2014–17–51, 

Amendment 39–17999 (79 FR 64088, October 

28, 2014), with new service information. For 

airplanes on which an inspection required by 

paragraph (g) or (j) of AD 2014–03–17, 

Amendment 39–17754 (79 FR 9389, February 

19, 2014), has been done as of November 12, 

2014 (the effective date of AD 2014–17–51), 

and on which any incorrectly oriented 

fastener, but no fractured fastener, was 

found: Except as provided by paragraph (i)(3) 

of this AD, do a detailed visual inspection of 

all inboard flap fasteners of the hinge-box 

forward fitting at WS 76.50 and WS 127.25, 

on both wings, to determine if the fasteners 

are intact (non-fractured, with intact fastener 

head). Inspect within 10 flight cycles after 

November 12, 2014, or within 100 flight 

cycles after the most recent inspection done 

as required by AD 2014–03–17, whichever 

occurs first. Inspect in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraph (g) of this AD. As of the effective 

date of this AD, only use Bombardier Alert 

Service Bulletin A604–57–006, Revision 04, 

dated November 12, 2014, including 

Appendices 1 and 2, dated September 26, 

2013; or Bombardier Alert Service Bulletin 

A605–57–004, Revision 04, dated November 

12, 2014, including Appendices 1 and 2, 

dated September 26, 2013; as applicable; for 

the actions required by this paragraph. 

(1) If all fasteners are found intact, repeat 

the inspection thereafter at intervals not to 

exceed 10 flight cycles, until the 

requirements of paragraph (i)(1) or (k) of this 

AD have been done. 

(2) If any fastener is found fractured: Before 

further flight, remove and replace all forward 

and aft fasteners at WS 76.50 and WS 127.25, 

regardless of condition or orientation, on 

both wings, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraph (g) of this AD. As of the effective 

date of this AD, only use Bombardier Alert 

Service Bulletin A604–57–006, Revision 04, 

dated November 12, 2014, including 

Appendices 1 and 2, dated September 26, 

2013; or Bombardier Alert Service Bulletin 

A605–57–004, Revision 04, dated November 

12, 2014, including Appendices 1 and 2, 

dated September 26, 2013; as applicable; for 

the actions required by this paragraph. After 

replacement of all fasteners as required by 

this paragraph, no further action is required 

by this AD. 

(i) Retained Terminating Action, With New 

Service Information 

This paragraph restates the terminating 

action specified in paragraph (i) of AD 2014– 

17–51, Amendment 39–17999 (79 FR 64088, 

October 28, 2014), with new service 

information. 

(1) Replacement of all forward and aft 

fasteners at WS 76.50 and WS 127.25, on 

both wings, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraph (g) of this AD, terminates the 

requirements of this AD. As of the effective 

date of this AD, only use Bombardier Alert 

Service Bulletin A604–57–006, Revision 04, 

dated November 12, 2014, including 

Appendices 1 and 2, dated September 26, 

2013; or Bombardier Alert Service Bulletin 

A605–57–004, Revision 04, dated November 

12, 2014, including Appendices 1 and 2, 

dated September 26, 2013; as applicable; for 

the actions specified in this paragraph. 

(2) Accomplishment of the applicable 

requirements of this AD constitutes 

terminating action for the requirements of AD 

2014–03–17, Amendment 39–17754 (79 FR 

9389, February 19, 2014), for that airplane 

only. 

(3) Replacement of all fractured and 

incorrectly oriented fasteners before 

November 12, 2014 (the effective date of AD 

2014–17–51, Amendment 39–17999 (79 FR 

64088, October 28, 2014)), as provided by 

paragraph (i) or (k) of AD 2014–03–17, 

Amendment 39–17754 (79 FR 9389, February 

19, 2014), is acceptable for compliance with 

the requirements of this AD. 

(j) Retained Special Flight Permit 

Prohibition 

This paragraph restates the requirements of 

paragraph (j) of AD 2014–17–51, Amendment 

39–17999 (79 FR 64088, October 28, 2014). 

Special flight permits to operate the airplane 

to a location where the airplane can be 

repaired in accordance with sections 21.197 

and 21.199 of the Federal Aviation 

Regulations (14 CFR 21.197 and 21.199) are 

not allowed. 

(k) New Requirement of This AD: PostInspection Fastener Replacement 

For airplanes on which incorrectly 

oriented fasteners were found during any 

inspection required by paragraph (g), (g)(3), 

(h), or (h)(1) of this AD, but none were found 

to be fractured: Within 24 months after the 

effective date of this AD, remove and replace 

all forward and aft fasteners at WS 76.50 and 

WS 127.25, regardless of condition or 

orientation, on both wings, in accordance 

with the Accomplishment Instructions of 

Bombardier Alert Service Bulletin A604–57– 

006, Revision 04, dated November 12, 2014, 

including Appendices 1 and 2, dated 

September 26, 2013 (for serial numbers 5301 

through 5665 inclusive); or Bombardier Alert 

Service Bulletin A605–57–004, Revision 04, 

dated November 12, 2014, including 

Appendices 1 and 2, dated September 26, 

2013 (for serial numbers 5701 through 5920 

inclusive). Accomplishing the requirements 

of this paragraph terminates the requirements 

of this AD. 

(l) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraphs (g), (h), and 

(i)(1) of this AD, if those actions were 

performed before the effective date of this AD 

using the applicable service information 

identified in paragraphs (l)(1)(i) and (l)(1)(ii) 

of this AD, which are not incorporated by 

reference in this AD. 

(i) Bombardier Alert Service Bulletin 

A604–57–006, Revision 03, dated August 19, 

2014, including Appendices 1 and 2, dated 

September 26, 2013. 

(ii) Bombardier Alert Service Bulletin 

A605–57–004, Revision 03, dated August 19, 

2014, including Appendices 1 and 2, dated 

September 26, 2013. 

(2) This paragraph provides credit for 

actions required by paragraph (k) of this AD, 

if those actions were done before the effective 

date of this AD using the applicable service 

information identified in paragraphs (l)(2)(i) 

through (l)(2)(iv) of this AD. 

(i) Bombardier Alert Service Bulletin 

A604–57–006, Revision 01, dated September 

26, 2013, including Appendices 1 and 2, 

dated September 26, 2013, which is 

incorporated by reference in AD 2014–03–17, 

Amendment 39–17754 (79 FR 9389, February 

19, 2014). 

(ii) Bombardier Alert Service Bulletin 

A604–57–006, Revision 02, dated January 22, 

2014, including Appendices 1 and 2, dated 

September 26, 2013, which is incorporated 

by reference in AD 2014–17–51, Amendment 

39–17999 (79 FR 64088, October 28, 2014). 

(iii) Bombardier Alert Service Bulletin 

A605–57–004, Revision 01, dated September 

26, 2013, including Appendices 1 and 2, 

dated September 26, 2013, which is 

incorporated by reference in AD 2014–03–17, 

Amendment 39–17754 (79 FR 9389, February 

19, 2014). 

(iv) Bombardier Alert Service Bulletin 

A604–57–004, Revision 02, dated January 22, 

2014, including Appendices 1 and 2, dated 

September 26, 2013, which is incorporated 

by reference in AD 2014–17–51, Amendment 

39–17999 (79 FR 64088, October 28, 2014). 

(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. 

(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 previously approved for AD 

2014–17–51, Amendment 39–17999 (79 FR 

64088, October 28, 2014), are acceptable for 

the corresponding requirements of 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 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules 63145 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, New York ACO, ANE–170, 

FAA; or Transport Canada Civil Aviation 

(TCCA); or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Emergency Airworthiness Directive CF– 

2014–27R1, dated August 29, 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–2015–3988. 

(2) For service information identified in 

this 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 

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 October 

6, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–26222 Filed 10–16–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4112; Directorate 

Identifier 2014–SW–043–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (previously Eurocopter 

France) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2010–23– 

02 for Eurocopter France (now Airbus 

Helicopters) Model SA–365N, SA– 

365N1, AS–365N2, and AS 365 N3 

helicopters. AD 2010–23–02 currently 

requires amending the Limitations 

section of the Rotorcraft Flight Manual 

(RFM) to limit the never-exceed velocity 

(VNE) to 150 Knots Indicated Air Speed 

(KIAS) and to add a 1,500 ft/minute rate 

of descent (R/D) limitation beyond 140 

KIAS. Since we issued AD 2010–23–02, 

a design change designated as 

modification (MOD) 0755B28 improved 

the dynamic behavior of the horizontal 

stabilizer such that AD actions are not 

required. This proposed AD would 

retain the requirements of AD 2010–23– 

01 and revise the applicability to 

exclude helicopters with MOD 0755B28. 

These proposed actions are intended to 

exclude certain helicopters from the 

applicability and restrict the VNE on 

other helicopters to prevent failure of 

the horizontal stabilizer and subsequent 

loss of control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by December 18, 

2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov in Docket No. 

FAA–2015–4112; or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

European Aviation Safety Agency 

(EASA) AD, the economic 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 service information identified in 

this proposed AD, contact Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax 

(972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may review service information at 

the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy., Room 6N–321, Fort Worth, 

Texas 76177. 

FOR FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 10101 

Hillwood Pkwy., Fort Worth, Texas 

76177; telephone (817) 222–5110; email 

robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

On October 15, 2010, we issued AD 

2010–23–02, Amendment 39–16491 (75 

FR 68169, November 5, 2010) for 

Eurocopter France (now Airbus 

Helicopters) Model SA–365N, SA– 

365N1, AS–365N2, and AS 365 N3 

helicopters. AD 2010–23–02 requires 

amending the Limitations section of the 

RFM to limit the VNE to 150 KIAS and 

to add a 1,500 ft/minute R/D limitation 

beyond 140 KIAS and installing one or 

more placards on the cockpit instrument 

panel in full view of the pilot and 

copilot. AD 2010–23–01 was prompted 

by failures of the horizontal stabilizers 

on then-recently delivered Model AS 

365 N3 helicopters due to a vibration 

phenomenon that may arise during the 

descent flight phases at high speed 

regardless of the stabilizer installed. 

Those actions were intended to prevent 

failure of the horizontal stabilizer and 

subsequent loss of control of the 

helicopter. 

Actions Since AD 2010–23–02 Was 

Issued 

Since we issued AD 2010–23–01 (75 

FR 68169, November 5, 2010), 

Eurocopter France changed its name to 

Airbus Helicopters. EASA, which is the 


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