Federal Register / Vol. 79, No. 144 / Monday, July 28, 2014 / Rules and Regulations 43607 

(i) Modification Prior to CFRP Door 

Installation 

At the applicable time specified in 

paragraph (i)(1) or (i)(2) of this AD: Modify 

the CFRP MLG outboard doors and 

attachment to the MLG, in accordance with 

Part 2 of the Accomplishment Instructions of 

Fokker Service Bulletin SBF100–52–090, 

dated November 17, 2011, including Fokker 

Manual Change Notification F100–147, dated 

October 28, 2011, as revised by Fokker 

Service Bulletin Change Notification 

SBF100–52–090/01, dated January 24, 2012. 

Accomplishing the modification in this 

paragraph terminates the inspection required 

by paragraph (g) of this AD. 

(1) For airplanes on which a CFRP MLG 

outboard door is installed as of the effective 

date of this AD: Do the modification within 

24 months after the effective date of this AD. 

(2) For airplanes on which an aluminum 

door is installed as of the effective date of 

this AD: Do the modification prior to the 

installation of the CFRP MLG outboard door. 

Note 1 to paragraph (i) of this AD: The 

aluminum MLG outboard doors and the 

CFRP MLG outboard doors are two-way 

interchangeable. 

(j) Parts Installation Prohibition 

As of the effective date of this AD, do not 

install on any airplane an MLG outboard 

door having part number (P/N) D13310–401 

through –418, or any MLG outboard door 

assembly having P/N D13312–401 through 

–410. 

Note 2 to paragraph (j) of this AD: Civil 

Aviation Authority-Netherlands (CAA–NL) 

AD NL–2006–001, dated January 5, 2006 

(European Aviation Safety Agency (EASA) 

approval 2006–002), contains guidance for 

modifying spare MLG outboard door 

assemblies having P/N D13312–401 through 

–410, to P/N D13312–7XX standard, as 

specified in the Accomplishment 

Instructions of Fokker Component Service 

Bulletin D13312–52–09, December 12, 2005, 

which is not incorporated by reference in this 

AD. 

(k) Parts Installation Limitation 

As of the effective date of this AD, do not 

install on any airplane a P/N D13310–701 

through –708 MLG outboard door, or a P/N 

D13312–702 through –711 MLG outboard 

door assembly, unless the part has been 

inspected for cracks in the recessed bolt 

heads, all applicable corrective actions have 

been done, and the CFRP MLG outboard door 

has been modified, in accordance with the 

Accomplishment Instructions of Fokker 

Component Service Bulletin D13312–52–015, 

dated November 17, 2011. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; fax 425–227–1149. 

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

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Fokker Services B.V.’s EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information EASA 

Airworthiness Directive 2012–0023, dated 

February 6, 2012, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0007-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

paragraphs (n)(3) and (n)(4) of this AD. 

(n) 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) Fokker Component Service Bulletin 

D13312–52–015, dated November 17, 2011. 

(ii) Fokker Service Bulletin SBF100–52– 

090, dated November 17, 2011, including 

Fokker Manual Change Notification F100– 

147, dated October 28, 2011. 

(iii) Fokker Service Bulletin Change 

Notification SBF100–52–090/01, dated 

January 24, 2012. The page number shown on 

the first page of this document should read 

‘‘Page 1 of 2.’’ 

(3) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 1357, 

2130 EL Hoofddorp, the Netherlands; 

telephone +31 (0)88–6280–350; fax +31 

(0)88–6280–111; email technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.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 June 25, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–17297 Filed 7–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1024; Directorate 

Identifier 2013–NM–140–AD; Amendment 

39–17909; AD 2014–15–07] 

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 DHC–8–102, 

–103, –106, –201, –202, –301, –311, and 

–315 airplanes. This AD was prompted 

by reports of a fractured wing-tofuselage strut attachment joint bolt. This 

AD requires a torque check of all wingto-fuselage strut attachment joint bolts, 

and repair or replacement if necessary. 

For certain airplanes, this AD also 

requires a detailed inspection for 

corrosion, damage, and wear of each 

wing-to-fuselage strut attachment joint 

bolt and associated hardware, and 

replacement if necessary; and a 

borescope inspection for corrosion and 

damage of the bore hole and barrel nut 

threads, and repair or replacement if 

necessary. We are issuing this AD to 

detect and correct fractured strut 

attachment joint bolts, which could 

result in reduced structural integrity of 

the wing-to-fuselage strut attachment 

joint and subsequent loss of the wing. 

DATES: This AD becomes effective 

September 2, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 2, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-1024- 


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43608 Federal Register / Vol. 79, No. 144 / Monday, July 28, 2014 / Rules and Regulations 

0002 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., 

Q-Series Technical Help Desk, 123 

Garratt Boulevard, Toronto, Ontario 

M3K 1Y5, Canada; telephone 416–375– 

4000; fax 416–375–4539; email 

thd.qseries@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. 

FOR FURTHER INFORMATION CONTACT: 

Jeffrey Zimmer, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE– 

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590; telephone (516) 228–7306; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Bombardier, Inc. Model 

DHC–8–102, –103, –106, –201, –202, 

–301, –311, and –315 airplanes. The 

NPRM published in the Federal 

Register on December 6, 2013 (78 FR 

73462). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2013–17R1, 

dated June 27, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model 

DHC–8–102, –103, –106, –201, –202, 

–301, –311, and –315 airplanes. The 

MCAI states: 

There have been two in-service reports of 

a wing-to-fuselage strut attachment joint bolt 

found fractured during routine maintenance. 

Laboratory examination of one fractured bolt 

revealed that the fracture was attributed to 

stress corrosion cracking. 

Failure of the bolts could compromise the 

structural integrity of the wing-to-fuselage 

strut attachment joint and could lead to a 

subsequent loss of the wing. 

This [Canadian] AD mandates the 

inspection and rectification, as required, of 

the wing-to-fuselage strut attachment joint 

bolts and associated hardware. 

* * * * * 

Required actions include a torque check 

of wing-to-fuselage strut attachment 

joint bolts, and repair or replacement if 

necessary. For certain airplanes, 

required actions include a detailed 

inspection for corrosion, damage 

(including but not limited to scratching, 

cracking, pitting, cross threads), and 

wear of each wing-to-fuselage strut 

attachment joint bolt and associated 

hardware, and replacement if necessary; 

and a borescope inspection for corrosion 

and damage of the bore hole and barrel 

nut threads, and repair or replacement 

if necessary. You may examine the 

MCAI in the AD docket on the Internet 

at http://www.regulations.gov/

#!documentDetail;D=FAA-2013-1024- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (78 FR 73462, 

December 6, 2013) and the FAA’s 

response to each comment. 

Request To Extend Compliance Time 

An anonymous commenter requested 

that we extend the compliance times 

from 2,000 flight cycles or 12 months, 

to 4,000 flight cycles or 24 months, after 

the effective date of the AD, in order to 

coincide with their scheduled ‘‘C’’ 

checks. 

We do not agree with the commenter’s 

request to extend the compliance time. 

We have determined that the 

compliance time, as proposed, 

represents the maximum interval of 

time allowable for the affected airplanes 

to continue to safely operate before the 

modification is done. We have not 

changed this AD in this regard. 

Request To Give Credit for Previous 

Compliance 

An anonymous commenter requested 

that we allow credit for actions 

accomplished using deHavilland Dash 8 

Series 100 Task Card Number 5730/04B, 

dated February 6, 2012, if the actions 

were done before the date the final rule 

becomes effective. 

We agree with the request. We have 

redesignated paragraph (j) of the 

proposed AD (78 FR 73462, December 6, 

2013) as paragraph (j)(1) of this AD, and 

have added new paragraph (j)(2) to this 

AD to allow credit for actions 

accomplished prior to the effective date 

of this AD using deHavilland Dash 8 

Series 100 Task Card Number 5730/04B, 

dated February 6, 2012. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In the NPRM (78 FR 73462, December 

6, 2013), we proposed to prevent the use 

of repairs that were not specifically 

developed to correct the unsafe 

condition, by requiring that the repair 

approval provided by the State of 

Design Authority or its delegated agent 

specifically refer to this FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

NPRM. 

No comments were provided to the 

NPRM (78 FR 73462, December 6, 2013) 

about these proposed changes. However, 

a comment was provided for an NPRM 

having Directorate Identifier 2012–NM– 

101–AD (78 FR 78285, December 26, 

2013). The commenter stated the 

following: ‘‘The proposed wording, 

being specific to repairs, eliminates the 

interpretation that Airbus messages are 

acceptable for approving minor 

deviations (corrective actions) needed 

during accomplishment of an AD 

mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 


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Federal Register / Vol. 79, No. 144 / Monday, July 28, 2014 / Rules and Regulations 43609 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed the 

paragraph and retitled it ‘‘Contacting the 

Manufacturer.’’ This paragraph now 

clarifies that for any requirement in this 

AD to obtain corrective actions from a 

manufacturer, the action must be 

accomplished using a method approved 

by the FAA, TCCA, or Bombardier’s 

TCCA Design Approval Organization 

(DAO). 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DAO, the approval must include 

the DAO-authorized signature. The DAO 

signature indicates that the data and 

information contained in the document 

are TCCA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DAO-authorized signature approval are 

not TCCA-approved, unless TCCA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

Other commenters to the NPRM 

having Directorate Identifier 2012–NM– 

101–AD (78 FR 78285, December 26, 

2013) pointed out that in many cases the 

foreign manufacturer’s service bulletin 

and the foreign authority’s MCAI might 

have been issued some time before the 

FAA AD. Therefore, the DOA might 

have provided U.S. operators with an 

approved repair, developed with full 

awareness of the unsafe condition, 

before the FAA AD is issued. Under 

these circumstances, to comply with the 

FAA AD, the operator would be 

required to go back to the 

manufacturer’s DOA and obtain a new 

approval document, adding time and 

expense to the compliance process with 

no safety benefit. 

Based on these comments, we 

removed the requirement that the DAHprovided repair specifically refer to this 

AD. Before adopting such a 

requirement, the FAA will coordinate 

with affected DAHs and verify they are 

prepared to implement means to ensure 

that their repair approvals consider the 

unsafe condition addressed in this AD. 

Any such requirements will be adopted 

through the normal AD rulemaking 

process, including notice-and-comment 

procedures, when appropriate. We also 

have decided not to include a generic 

reference to either the ‘‘delegated agent’’ 

or ‘‘DAH with State of Design Authority 

design organization approval,’’ but 

instead we have provided the specific 

delegation approval granted by the State 

of Design Authority for the DAH 

throughout this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

73462, December 6, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 73462, 

December 6, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 94 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD. 

We also estimate that it would take 

about 107 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts would 

cost about $5,476 per product. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be 

$1,369,674, or $14,571 per product. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the repairs or replacements 

specified in this AD. 

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 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 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-1024; 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 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 


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43610 Federal Register / Vol. 79, No. 144 / Monday, July 28, 2014 / Rules and Regulations 

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): 

2014–15–07 Bombardier, Inc.: Amendment 

39–17909. Docket No. FAA–2013–1024; 

Directorate Identifier 2013–NM–140–AD. 

(a) Effective Date 

This AD becomes effective September 2, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–102, –103, –106, –201, –202, –301, 

–311, and –315 airplanes; certificated in any 

category; serial numbers 003 through 672 

inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports of a 

fractured wing-to-fuselage strut attachment 

joint bolt. We are issuing this AD to detect 

and correct fractured strut attachment joint 

bolts, which could result in reduced 

structural integrity of the wing-to-fuselage 

strut attachment joint and subsequent loss of 

the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Torque Check 

At the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD: Do a 

torque check of the wing-to-fuselage strut 

attachment joint bolts, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 8–57–47, 

Revision A, dated May 29, 2013. 

(1) For airplanes that have accumulated 

fewer than 40,000 total flight cycles, and 

have less than 15 years in service since new, 

as of the effective date of this AD: Do the 

torque check before the accumulation of 

42,000 total flight cycles, or within 16 years 

in service since new, whichever occurs first. 

(2) For airplanes that have accumulated 

40,000 total flight cycles or more, or have 15 

years or more in service since new, as of the 

effective date of this AD: Do the torque check 

within 2,000 flight cycles or 12 months after 

the effective date of this AD, whichever 

occurs first. 

(h) Inspection and Corrective Actions 

(1) If only one bolt fails the torque check 

required by paragraph (g) of this AD, before 

further flight, replace the bolt, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 8–57–47, 

Revision A, dated May 29, 2013; and before 

further flight do the actions specified in 

paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. 

(2) If more than one bolt fails the torque 

check required by paragraph (g) of this AD, 

before further flight, repair 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 

DAO-authorized signature. 

(3) If all bolts pass the torque check 

required by paragraph (g) of this AD, before 

further flight, do the actions specified in 

paragraphs (h)(3)(i) and (h)(3)(ii) of this AD, 

as applicable. 

(i) Do a detailed inspection for corrosion, 

damage (including but not limited to 

scratching, cracking, pitting, and cross 

threads, etc.), and wear, of each wing-tofuselage strut attachment joint bolt and 

associated hardware, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–57–47, Revision A, dated 

May 29, 2013. If any bolt or hardware has 

corrosion, damage, or wear, before further 

flight, replace the affected part, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 8–57–47, 

Revision A, dated May 29, 2013. 

(ii) Do a borescope inspection for corrosion 

and damage (including but not limited to 

scratching, cracking, pitting, and cross 

threads, etc.) of the bore hole and barrel nut 

threads, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–57–47, Revision A, dated 

May 29, 2013, except as provided by 

paragraph (i) of this AD. 

(A) If any corrosion or damage is found in 

the barrel nut threads, before further flight, 

replace the barrel nut, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–57–47, Revision A, dated 

May 29, 2013, except as provided by 

paragraph (i) of this AD. 

(B) If any corrosion or damage is found in 

the bore of the hole, before further flight, 

repair using a method approved by the 

Manager, New York ACO, ANE–170, Engine 

and Propeller Directorate, FAA; or TCCA; or 

Bombardier, Inc.’s TCCA DAO. If approved 

by the DAO, the approval must include the 

DAO-authorized signature. 

(i) Exception to Service Information 

Where Bombardier Service Bulletin 8–57– 

47, Revision A, dated May 29, 2013, specifies 

to contact the manufacturer for repair 

information, this AD requires repairing 

before further flight using a method approved 

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

Engine and Propeller Directorate, FAA; or 

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

and, if approved by the DAO, the approval 

must include the DAO-authorized signature. 

(j) Credit for Previous Actions 

(1) This paragraph provides credit for 

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

this AD, if those actions were performed 

before the effective date of this AD using 

Bombardier Service Bulletin 8–57–47, dated 

March 16, 2012, which is not incorporated by 

reference in this AD. 

(2) This paragraph provides credit for 

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

this AD if those actions were performed 

before the effective date of this AD using de 

Havilland Inc. Dash 8 Series 100 

Maintenance Task Card Number 5730/04B, 

dated February 6, 2012, which is not 

incorporated by reference in this AD. 

(k) 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 

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 

TCCA; or Bombardier, Inc.’s TCCA DAO. If 

approved by the DAO, the approval must 

include the DAO-authorized signature. 

(l) Special Flight Permits 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–17R1, 

dated June 27, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-1024-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

paragraphs (n)(3) and (n)(4) of this AD. 

(n) 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. 


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Federal Register / Vol. 79, No. 144 / Monday, July 28, 2014 / Rules and Regulations 43611 

(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 8–57–47, 

Revision A, dated May 29, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@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 July 15, 

2014. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–17316 Filed 7–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0253; Directorate 

Identifier 2013–NM–257–AD; Amendment 

39–17908; AD 2014–15–06] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 747–100B 

SUD, 747–200B, 747–300, 747–400, and 

747–400D series airplanes. This AD was 

prompted by an evaluation by the 

design approval holder (DAH) 

indicating that the upper deck tension 

ties are subject to widespread fatigue 

damage (WFD). This AD requires 

repetitive inspections for cracking in the 

upper deck tension ties, and related 

investigative and corrective actions if 

necessary; tension tie replacement; and 

post-replacement repetitive inspections 

for cracking in the upper deck tension 

ties, and related investigative and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

fatigue cracking of the upper deck 

tension ties. Severed or disconnected 

tension ties at multiple locations could 

result in rapid decompression and loss 

of structural integrity of the airplane. 

DATES: This AD is effective September 2, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 2, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.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– 

0253; 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

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 20590. 

FOR FURTHER INFORMATION CONTACT: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6428; fax: 

425–917–6590; email: 

nathan.p.weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 747–100B SUD, 747–200B, 747– 

300, 747–400, 747–400D series 

airplanes. The NPRM published in the 

Federal Register on April 23, 2014 (79 

FR 22596). The NPRM was prompted by 

an evaluation by the DAH indicating 

that the upper deck tension ties are 

subject to WFD. The NPRM proposed to 

require repetitive inspections for 

cracking in the upper deck tension ties, 

and related investigative and corrective 

actions if necessary; tension tie 

replacement; and post-replacement 

repetitive inspections for cracking in the 

upper deck tension ties, and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct fatigue cracking of the 

upper deck tension ties. Severed or 

disconnected tension ties at multiple 

locations could result in rapid 

decompression and loss of structural 

integrity of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

The Boeing Company supported the 

NPRM (79 FR 22596, April 23, 2014). 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

22596, April 23, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 22596, 

April 23, 2014). 

Costs of Compliance 

We estimate that this AD affects 76 

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 

Inspections (pre-modification 

and post-modification).

Up to 164 work-hours × $85 

per hour = $13,940 per inspection cycle.

$0 Up to $13,940 per inspection 

cycle.

Up to $1,059,440 per inspection cycle. 


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