64088 Federal Register / Vol. 79, No. 208 / Tuesday, October 28, 2014 / Rules and Regulations 

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): 

2014–21–07 Bombardier, Inc.: Amendment 

39–18000. Docket No. FAA–2014–0287; 

Directorate Identifier 2013–NM–247–AD. 

(a) Effective Date 

This AD becomes effective December 2, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Bombardier, Inc. 

airplanes specified in paragraphs (c)(1), 

(c)(2), and (c)(3) of this AD, certificated in 

any category. 

(1) Model CL–600–2C10 (Regional Jet 

Series 700, 701, & 702) airplanes, serial 

numbers 10303 through 10333 inclusive. 

(2) Model CL–600–2D24 (Regional Jet 

Series 900) airplanes, serial numbers 15257 

through 15284 inclusive. 

(3) Model CL–600–2E25 (Regional Jet 

Series 1000) airplanes, serial numbers 19011 

through 19024 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 52, Doors. 

(e) Reason 

This AD was prompted by a report that 

certain parts of the aft baggage door did not 

conform to the design specifications and 

were of degraded strength. We are issuing 

this AD to prevent cracking and deformations 

of stop fittings and striker plates, which 

could result in the opening of the aft baggage 

bay door and rapid decompression or 

reduced controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections of the Aft Baggage Bay Door 

Stop Fittings and Striker Plates 

Within 600 flight hours or 6 months after 

the effective date of this AD, whichever 

occurs first: Do a detailed visual inspection 

for cracking and deformations of the stop 

fittings and striker plates of the aft baggage 

bay door, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–52–037, Revision B, 

dated September 16, 2013. Repeat the 

inspection thereafter at intervals not to 

exceed 2,000 flight hours or 12 months, 

whichever occurs first, until the terminating 

action specified in paragraph (h) of this AD 

has been accomplished. If a crack or 

deformation is found on a stop fitting or 

striker plate, before further flight, replace the 

affected fittings and striker plates, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

670BA–52–037, Revision B, dated September 

16, 2013. 

(h) Terminating Action—Replacement of the 

Aft Baggage Bay Door Stop Fittings and 

Striker Plates 

Within 6,000 flight hours or 36 months, 

whichever occurs first, after the effective date 

of this AD: Replace the affected stop fittings 

and striker plates, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–52–037, Revision B, 

dated September 16, 2013. Replacement of 

the affected stop fittings and striker plates of 

the aft baggage bay door constitutes 

terminating action for the repetitive 

inspections required by paragraph (g) of this 

AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

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

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

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

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

Transport Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–37, dated 

November 28, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0287-0002. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Bombardier Service Bulletin 670BA–52– 

037, Revision B, dated September 16, 2013. 

(ii) Reserved. 

(3) 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. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on October 

13, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–25022 Filed 10–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0581; Directorate 

Identifier 2014–NM–167–AD; Amendment 

39–17999; AD 2014–17–51] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2B16 

airplanes. This emergency AD was sent 

previously to all known U.S. owners 

and operators of these airplanes. This 

AD 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. This AD also provides for 

optional terminating action for the 

requirements of the AD. This AD was 

prompted by reports of fractured 

fastener heads on the inboard flap 

hinge-box forward fitting at WS 76.50 

due to incorrect installation. We are 

issuing this AD to detect and correct 


asabaliauskas on DSK5VPTVN1PROD with RULES
Federal Register / Vol. 79, No. 208 / Tuesday, October 28, 2014 / Rules and Regulations 64089 

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: This AD is effective November 

12, 2014 to all persons except those 

persons to whom it was made 

immediately effective by Emergency AD 

2014–17–51, issued on August 19, 2014, 

which contained the requirements of 

this amendment. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications identified in this 

AD as of November 12, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of March 6, 2014 (79 FR 

9389, February 19, 2014). 

We must receive comments on this 

AD by December 12, 2014. 

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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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 referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0581; 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations Office (phone: 

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: 

Discussion 

On August 19, 2014, we issued 

Emergency AD 2014–17–51, which 

requires inspecting the inboard flap 

fasteners of the hinge-box forward 

fitting at 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. Emergency 

AD 2014–17–51 also provides for 

optional terminating action for the 

requirements of the AD. This emergency 

AD was sent previously to all known 

U.S. owners and operators of these 

airplanes. This action 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. This condition, 

if not corrected, 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. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Emergency Airworthiness Directive CF– 

2014–27, dated August 15, 2014 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition on certain 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 AD CF–2013–39 

[dated December 6, 2013] [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 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. 

This [Canadian] AD is issued to reduce the 

initial and repetitive inspection intervals 

previously mandated in 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 

AD CF–2013–39R1 [dated August 15, 2014]. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2014–0581. 

Relevant Service Information 

We reviewed the following service 

information: 

• Bombardier Alert Service Bulletin 

A604–57–006, Revision 01, dated 

September 26, 2013, including 

Appendices 1 and 2, dated September 

26, 2013. 

• Bombardier Alert Service Bulletin 

A604–57–006, Revision 02, dated 

January 22, 2014, including Appendices 

1 and 2, dated September 26, 2013. 

• Bombardier Alert Service Bulletin 

A605–57–004, Revision 01, dated 

September 26, 2013, including 

Appendices 1 and 2, dated September 

26, 2013. 

• Bombardier Alert Service Bulletin 

A605–57–004, Revision 02, dated 

January 22, 2014, including Appendices 

1 and 2, dated September 26, 2013. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

Revision 02 of the service information 

instructs operators to contact 

Bombardier for repair procedures for 

certain configurations; paragraph (k)(2) 

of this AD addresses this issue. 

FAA’s Determination and AD 

Requirements 

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 


asabaliauskas on DSK5VPTVN1PROD with RULES
64090 Federal Register / Vol. 79, No. 208 / Tuesday, October 28, 2014 / Rules and Regulations 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Accomplishment of the 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 the airplanes 

identified in paragraph (c) of this AD. 

FAA AD 2014–03–17, Amendment 

39–17754 (79 FR 9389, February 19, 

2014), corresponds to Canadian AD CF– 

2013–39, dated December 6, 2013. FAA 

AD 2014–03–17 applies to Bombardier, 

Inc. Model CL–600–1A11 (CL–600), CL– 

600–2A12 (CL–601), and CL–600–2B16 

(CL–601–3A, CL–601–3R, and CL–604 

Variants) airplanes. Because of the 

urgency of this unsafe condition for the 

CL–604 Variant airplanes, we have 

determined that it is necessary to issue 

an emergency AD, only for CL–604 

Variant airplanes, to reduce the 

compliance times for the inspection 

required by AD 2014–03–17. 

Explanation of Applicability 

This AD applies to Bombardier, Inc. 

Model CL–600–2B16 airplanes with 

certain serial numbers. The CL–605 is a 

marketing designation for the 

Challenger CL–600–2B16, CL–604 

Variant, with Modsums 604DX10000, 

604DX20000, and 604DX30000 

incorporated, beginning with serial 

numbers 5701 and subsequent. All CL– 

604 and CL–605 airplanes are type 

certified as CL–600–2B16 airplanes. 

Therefore this AD applies to all CL– 

600–2B16 models in the specified serialnumber range. 

Differences Between This AD and the 

MCAI/Service Information 

Canadian Airworthiness Directive 

CF–2014–27, dated August 15, 2014, 

specifies to replace all forward and aft 

fasteners at WS 76.50 and 127.25 within 

24 months, if any incorrectly installed 

fasteners are found. We are considering 

requiring this replacement, which 

would terminate the actions required by 

this AD. However, the planned 

compliance time for the replacement 

would allow enough time to provide 

notice and opportunity for prior public 

comment on the merits of the 

replacement. 

Although the service information 

identified previously specifies that 

operators may contact the manufacturer 

for disposition of certain repair 

conditions, this AD requires operators to 

repair those conditions in accordance 

with a method approved by the FAA, or 

TCCA, or Bombardier, Inc.’s TCCA 

Design Approval Organization (DAO). 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because incorrect installation of the 

fasteners attaching the inboard flap 

hinge-box forward fitting may result in 

their premature failure, and possible 

detachment of the flap hinge box and 

the flap surface, and loss of control of 

the airplane. Therefore, we find that 

notice and opportunity for prior public 

comment are impracticable and that 

good cause exists for making this 

amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2014–0581 and Directorate 

Identifier 2014–NM–167–AD at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of 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 AD. 

Costs of Compliance 

We estimate that this AD affects 285 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection ................................ 1 work-hour × $85 per hour = $85 ......................................... $0 $85 $24,225 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Fastener replacement ...................... Up to 58 work-hours × $85 per hour = $4,930 ......................................... $0 $4,930 

According to the manufacturer, some 

of the costs of this 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, 


asabaliauskas on DSK5VPTVN1PROD with RULES
Federal Register / Vol. 79, No. 208 / Tuesday, October 28, 2014 / Rules and Regulations 64091 

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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will 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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2014–17–51 Bombardier, Inc.: Amendment 

39–17999; Docket No. FAA–2014–0581; 

Directorate Identifier 2014–NM–167–AD. 

(a) Effective Date 

This AD is effective November 12, 2014 to 

all persons except those persons to whom it 

was made immediately effective by 

Emergency AD 2014–17–51, issued on 

August 19, 2014, which contained the 

requirements of this amendment. 

(b) Affected ADs 

The requirements of this AD terminate the 

requirements of 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) Unsafe Condition 

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) Inspection: Airplanes Not Previously 

Inspected 

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 the effective date 

of this AD: Within 10 flight cycles after the 

effective date of this AD, 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 (nonfractured, 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, or Revision 02, dated 

January 22, 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, or Revision 02, dated 

January 22, 2014, including Appendices 1 

and 2, dated September 26, 2013 (for serial 

numbers 5701 through 5920 inclusive). 

(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 Bombardier 

Alert Service Bulletin A604–57–006, 

Revision 01, dated September 26, 2013, 

including Appendices 1 and 2, dated 

September 26, 2013, or Revision 02, dated 

January 22, 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, or Revision 02, dated 

January 22, 2014, including Appendices 1 

and 2, dated September 26, 2013 (for serial 

numbers 5701 through 5920 inclusive). After 

replacement of all fasteners as required by 

paragraph (g)(2) of this AD, no further action 

is required by this AD. 

(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) of this 

AD have been done. 

(h) Airplanes Previously Inspected, With 

Incorrectly Oriented Fastener(s) 

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 the 

effective date of this AD, 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 the effective date of this AD, 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 Bombardier Alert Service 

Bulletin A604–57–006, Revision 01, dated 

September 26, 2013, including Appendices 1 

and 2, dated September 26, 2013, or Revision 

02, dated January 22, 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, or Revision 

02, dated January 22, 2014, including 

Appendices 1 and 2, dated September 26, 

2013 (for serial numbers 5701 through 5920 

inclusive). 

(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) 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 Bombardier 

Alert Service Bulletin A604–57–006, 


asabaliauskas on DSK5VPTVN1PROD with RULES
64092 Federal Register / Vol. 79, No. 208 / Tuesday, October 28, 2014 / Rules and Regulations 

Revision 01, dated September 26, 2013, 

including Appendices 1 and 2, dated 

September 26, 2013, or Revision 02, dated 

January 22, 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, or Revision 02, dated 

January 22, 2014, including Appendices 1 

and 2, dated September 26, 2013 (for serial 

numbers 5701 through 5920 inclusive). After 

replacement of all fasteners as required by 

paragraph (h)(2) of this AD, no further action 

is required by this AD. 

(i) Terminating Action 

(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 Bombardier 

Alert Service Bulletin A604–57–006, 

Revision 01, dated September 26, 2013, 

including Appendices 1 and 2, dated 

September 26, 2013, or Revision 02, dated 

January 22, 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, or Revision 02, dated 

January 22, 2014, including Appendices 1 

and 2, dated September 26, 2013 (for serial 

numbers 5701 through 5920 inclusive); 

terminates the requirements of this AD. 

(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, before the effective date 

of this AD, of all fractured and incorrectly 

oriented fasteners, 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) Special Flight Permit 

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) Other FAA Provisions 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office, ANE–170, FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the ACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

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

using any approved AMOC, notify your 

appropriate principal inspector, or lacking a 

principal inspector, the manager of the local 

flight standards district office/certificate 

holding district office. The AMOC approval 

letter must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York Aircraft 

Certification Office, ANE–170, FAA; or the 

TCCA; or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(l) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Emergency Airworthiness Directive CF– 

2014–27, dated August 15, 2014, for related 

information. You may examine the MCAI on 

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

searching for and locating Docket No. FAA– 

2014–0581. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on November 12, 2014. 

(i) Bombardier Alert Service Bulletin 

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

2014, including Appendices 1 and 2, dated 

September 26, 2013. 

(ii) Bombardier Alert Service Bulletin 

A605–57–004, Revision 02, dated January 22, 

2014, including Appendices 1 and 2, dated 

September 26, 2013. 

(4) The following service information was 

approved for IBR on March 6, 2014 (79 FR 

9389, February 19, 2014). 

(i) Bombardier Alert Service Bulletin 

A604–57–006, Revision 01, dated September 

26, 2013, including Appendices 1 and 2, 

dated September 26, 2013. 

(ii) Bombardier Alert Service Bulletin 

A605–57–004, Revision 01, dated September 

26, 2013, including Appendices 1 and 2, 

dated September 26, 2013. 

(5) 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. 

(6) 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. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on October 

13, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–25018 Filed 10–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0548; Directorate 

Identifier 2013–NM–008–AD; Amendment 

39–18002; AD 2014–21–08] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model BD–700–1A11 

airplanes. This AD was prompted by a 

report that certain lanyards for the 

passenger oxygen masks are longer than 

the specified length, possibly leading to 

inactive oxygen masks in an emergency. 

This AD requires replacement of certain 

oxygen mask lanyards. We are issuing 

this AD to detect and correct lanyards 

of incorrect length, which might not 

activate the flow of oxygen in an 

emergency, resulting in injury to 

passengers. 

DATES: This AD becomes effective 

December 2, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 2, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0548 or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

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 referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 


asabaliauskas on DSK5VPTVN1PROD with RULES