Federal Register / Vol. 79, No. 239 / Friday, December 12, 2014 / Rules and Regulations 73805 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as a need to 

incorporate new revisions into the aircraft 

maintenance manual (AMM) or in the 

Limitations document of the FAA-approved 

maintenance program. The limitations were 

revised to incorporate new life limits for the 

fire extinguisher. These actions are required 

to ensure the continued operational safety of 

the affected airplanes. 

(f) Actions and Compliance 

(1) Actions retained from AD 2013–11–08, 

Amendment 39–17468 (78 FR 37701; June 24, 

2013) for all airplanes in the Applicability 

section of this AD: If the flap actuator has 

accumulated 3,500 hours time-in-service 

(TIS) or more since new or last overhauled 

or 7 years or more since new or last 

overhauled, whichever occurs first, 

replacement of the flap actuator (except part 

numbers 978.73.14.101 and 978.73.14.103) is 

required within 350 hours TIS after July 29, 

2013, (the effective date retained from AD 

2013–11–08) or 6 months after July 29, 2013, 

(the effective date retained from AD 2013– 

11–08), whichever occurs first. Flap actuators 

with less than 3,500 hours TIS or 7 years 

since new or last overhauled are covered by 

the airworthiness limitations document 

(ALS) requirement. 

(2) Actions new to this AD for all affected 

Models PC–6/B2–H2 and PC–6/B2–H4 

airplanes: Before further flight after January 

16, 2015 (the effective date of this AD) 

incorporate the maintenance requirements as 

specified in Section 04–00–00, Airworthiness 

Limitations, of Chapter 04, Airworthiness 

Limitations, of the Pilatus PC–6 Maintenance 

Manual, document number 01975, Revision 

19, dated May 31, 2014, into your FAAaccepted maintenance program (maintenance 

manual). 

(3) Actions new to this AD for all airplanes 

in the Applicability section of this AD except 

for the Models PC–6/B2–H2 and PC–6/B2–H4 

airplanes: Before further flight after January 

16, 2015 (the effective date of this AD) 

incorporate the maintenance requirements as 

specified in Pilatus ALS, document number 

02334, Revision 4, dated May 31, 2014, into 

your FAA-accepted maintenance program 

(maintenance manual). 

(4) Actions new to this AD for all airplanes 

in the Applicability section of this AD: 

(i) For airplanes with Halon Fire 

Extinguishers that have not yet reached the 

10 year life limit after January 16, 2015 (the 

effective date of this AD), when the Halon 

Fire Extinguisher reaches its life limit of 10 

years, before further flight, replace with an 

airworthy Halon Fire Extinguisher following 

Section 04–00–00, Airworthiness 

Limitations, of Chapter 04, Airworthiness 

Limitations, of the Pilatus PC–6 Maintenance 

Manual, document number 01975, Revision 

19, dated May 31, 2014; or Pilatus ALS 

document number 02334, Revision 4, dated 

May 31, 2014; as applicable. 

(ii) For airplanes with Halon Fire 

Extinguishers that have reached the 10 year 

life limit on or before January 16, 2015 (the 

effective date of this AD), within the next 6 

months after January 16, 2015 (the effective 

date of this AD), replace with an airworthy 

Halon Fire Extinguisher following Section 

04–00–00, Airworthiness Limitations, of 

Chapter 04, Airworthiness Limitations, of the 

Pilatus PC–6 Maintenance Manual, document 

number 01975, Revision 19, dated May 31, 

2014; or Pilatus ALS document number 

02334, Revision 4, dated May 31, 2014; as 

applicable. 

(iii) Repetitively, after replacing the 

airplanes Halon Fire Extinguisher as required 

in paragraphs (f)(4)(i) or (f)(4)(ii), within 10 

years after each last replacement, replace 

with an airworthy Halon Fire Extinguisher. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4059; fax: (816) 329– 

4090; email: doug.rudolph@faa.gov. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(h) Related Information 

Refer to European Aviation Safety Agency 

(EASA) AD No.: 2014–0181, dated July 31, 

2014, for related information. The MCAI can 

be found in the AD docket on the Internet at: 

http://www.regulations.gov/

#!docketDetail;D=FAA-2014-0717. 

(i) 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. 

(i) Pilatus Airworthiness Limitations 

document number 02334, Revision 4, dated 

May 31, 2014. The revision level of this 

document is indicated only in the Record of 

Revisions. 

(ii) Section 04–00–00, Airworthiness 

Limitations, of Chapter 04, Airworthiness 

Limitations, of the Pilatus PC–6 Maintenance 

Manual, document number 01975, Revision 

19, dated May 31, 2014. 

(3) For Pilatus Aircraft Limited service 

information identified in this AD, contact 

PILATUS AIRCRAFT LTD., Customer Liaison 

Manager, CH–6371 STANS, Switzerland; 

telephone: +41 (0) 41 619 65 80; fax: +41 (0) 

41 619 65 76; Internet: http://www.pilatusaircraft.com; email: fodermatt@pilatusaircraft.com. 

(4) You may view this service information 

at FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

(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 Kansas City, Missouri, on 

December 2, 2014. 

Robert Busto, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–28730 Filed 12–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0053; Directorate 

Identifier 2013–NM–174–AD; Amendment 

39–18047; AD 2014–25–05] 

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 777 

airplanes. This AD was prompted by 

reports of corroded, migrated, or broken 

spring pins of the girt bar floor fitting; 

in one case the broken pins prevented 

a door escape slide from deploying 

during a maintenance test. This AD 

requires replacing the existing spring 

pins at each passenger entry door at 

both girt bar floor fittings with new 

spring pins. We are issuing this AD to 

prevent broken or migrated spring pins 

of the girt bar floor fittings, which could 

result in improper deployment of the 

escape slide/raft and consequent delay 

and injury during evacuation of 

passengers and crew from the cabin in 

the event of an emergency. 

DATES: This AD is effective January 16, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 16, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 


rljohnson on DSK3VPTVN1PROD with RULES
73806 Federal Register / Vol. 79, No. 239 / Friday, December 12, 2014 / Rules and Regulations 

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, Washington. 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– 

0053; 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: Ana 

Martinez Hueto, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6592; 

fax: 425–917–6591; email: 

ana.m.hueto@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 777 airplanes. The NPRM 

published in the Federal Register on 

February 6, 2014 (79 FR 7103). The 

NPRM was prompted by reports of 

corroded, migrated, or broken spring 

pins of the girt bar floor fitting; in one 

case the broken pins prevented a door 

escape slide from deploying during a 

maintenance test. The NPRM proposed 

to require replacing the existing spring 

pins at each passenger entry door at 

both girt bar floor fittings with new 

spring pins. We are issuing this AD to 

prevent broken or migrated spring pins 

of the girt bar floor fittings, which could 

result in improper deployment of the 

escape slide/raft and consequent delay 

and injury during evacuation of 

passengers and crew from the cabin in 

the event of an emergency. 

Revised Service Information 

Since publication of the NPRM (79 FR 

7103, February 6, 2014), Boeing has 

issued Service Bulletin 777–52A0050, 

Revision 1, dated August 7, 2014. That 

revision states that no more work is 

necessary on airplanes changed in 

accordance with the original issue 

(Boeing Alert Service Bulletin 777– 

52A0050, dated June 18, 2013), which 

was specified as the appropriate source 

of service information in the NPRM. 

We have changed paragraphs (c) and 

(g) of this AD to specify Boeing Service 

Bulletin 777–52A0050, Revision 1, 

dated August 7, 2014; added a new 

paragraph (h) to this AD to give credit 

for actions done before the effective date 

of this AD using Boeing Alert Service 

Bulletin 777–52A0050, dated June 18, 

2013; and redesignated subsequent 

paragraphs accordingly. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 7103, 

February 6, 2014) and the FAA’s 

response to each comment. 

Request To Change Compliance Time 

Boeing asked that we change the 

compliance time in paragraph (g) of the 

NPRM (79 FR 7103, February 6, 2014) 

from 36 months to 1,175 days. Boeing 

stated that 1,175 days (3 years, 80 days) 

is consistent with the compliance time 

specified in Boeing Alert Service 

Bulletin 777–52A0050, dated June 18, 

2013. Boeing noted that this compliance 

time encompasses the 777 maintenance 

planning document C-check inspection 

interval of 1,125 days (3 years, 30 days) 

for structural items. Boeing added that 

this change is not significant. 

American Airlines (AA) asked that we 

change the compliance time to match 

the Maintenance Review Board (MRB) 

limit of 1,125 days, which would allow 

AA’s maintenance to be scheduled at 

regular maintenance visits without any 

undue burden on current flight 

schedules. 

We agree with changing the 

compliance time to coincide with 

regular maintenance inspection 

intervals. However, instead of 

specifying 1,175 days, we worked in 

conjunction with Boeing to determine 

that a 37-month compliance time is 

appropriate. We have changed 

paragraph (g) of this AD accordingly. 

Request To Limit Parts Installation 

Prohibition 

Delta Airlines (Delta) asked that we 

revise paragraph (h) of the NPRM (79 FR 

7103, February 6, 2014), which is 

paragraph (i) of this AD, to prohibit 

installation of the specified spring pins 

only in the locations being addressed by 

this AD. Delta stated that this 

clarification would allow the use of part 

number (P/N) MS39086–261 or P/N 

MS16562–252 in locations not subject to 

the actions in the NPRM. Delta added 

that the proposed language would 

prevent the use of these pins anywhere 

on the applicable Model 777 airplanes. 

We agree to specify the location on 

the airplane where installation of the 

spring pins is prohibited. We have 

changed paragraph (i) of this AD 

accordingly. 

Request To Revise Parts Installation 

Prohibition to Pertain to Unmodified 

Airplanes Only 

AA asked that we prohibit installation 

of spring pins only on airplanes 

modified in accordance with Boeing 

Service Bulletin 777–52A0050, Revision 

1, dated August 7, 2014, and allow 

installation of the spring pins on 

unmodified airplanes. AA added that 

the Boeing Model 777 Illustrated Parts 

Catalog (IPC) currently identifies spring 

pins having P/N MS16562–252 as valid 

parts for installation on unmodified 

airplanes. AA added that, since the 

analysis of broken spring pins has 

shown that they have failed due to 

stress corrosion, it should be acceptable 

to install a new pin in an unmodified 

airplane because the airplane will be 

modified within a set amount of time. 

We do not agree to allow installation 

of the spring pins having part number 

MS39086–261 or MS16562–252 on 

unmodified airplanes. In general, once 

we have determined that an unsafe 

condition exists, we do not allow that 

condition to be introduced into the fleet. 

In developing the technical information 

on which every AD is based, we 

consider the availability of replacement 

parts that the AD will require to be 

installed. Since we have determined 

that replacement parts are available to 

operators, this AD prohibits installation 

of the unsafe parts. We have not 

changed this AD in this regard. 

Request To Define Configuration/Parts 

Control 

Singapore Airlines asked for an 

explanation of how Boeing ensures that 

the affected spring pins are not 

delivered to operators since the girt bar 

assembly includes the spring pins. 

FedEx asked that we revise the NPRM 

(79 FR 7103, February 6, 2014) either to 

specifically state that no reidentification 

of the floor fitting assemblies is 

required, or to provide a specific 

reidentification process. FedEx Express 

also asked that the issue of parts 


rljohnson on DSK3VPTVN1PROD with RULES
Federal Register / Vol. 79, No. 239 / Friday, December 12, 2014 / Rules and Regulations 73807 

identification as specified in the 

referenced service information (Boeing 

Alert Service Bulletin 777–52A0050, 

dated June 18, 2013), be resolved. FedEx 

noted ‘‘a vague requirement’’ to identify 

accomplishment of the service bulletin 

on the part but there are no specific 

instructions. FedEx stated this could 

result in the part being inadvertently 

returned to a pre-modification 

condition. FedEx recognized that 

ensuring compliance lies in the control 

of the spring pins, not the floor fitting 

assemblies. FedEx stated that there is no 

value added by identifying the part after 

the change is made because Boeing did 

not provide a step in the Work 

Instructions with a location to apply 

this identification. 

We acknowledge the commenter’s 

concerns. Since issuance of the NPRM 

(79 FR 7103, February 6, 2014), Boeing 

has updated its IPC and Boeing Service 

Bulletin 777–52A0050, Revision 1, 

dated August 7, 2014, to clarify 

appropriate parts installation. In 

addition, Boeing Service Bulletin 777– 

52A0050, Revision 1, dated August 7, 

2014, includes Work Instructions for 

applying the part identification. We 

have not changed this AD in this regard. 

Concern Regarding Parts Availability 

FedEx expressed concern about the 

ability of operators to obtain the 

required parts since Boeing currently 

restricts the part’s availability. FedEx 

noted that it has an adequate supply. 

We consider the compliance times in 

this AD to be adequate to allow 

operators to acquire parts to have on 

hand for replacing the affected spring 

pins. Therefore, we have determined 

that, due to the safety implications and 

consequences associated with corroded, 

migrated, or broken spring pins, the 

existing pins must be replaced within 

37 months after the effective date of this 

AD. We have not changed this AD 

regarding this issue. 

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, 

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 7103, 

February 6, 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 7103, 

February 6, 2014). 

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 189 

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 

Replacement ................. Up to 40 work-hours × $85 per hour = Up to 

$3,400.

$0 Up to $3,400 ........................ Up to $642,600. 

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 

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): 

2014–25–05 The Boeing Company: 

Amendment 39–18047 ; Docket No. 

FAA–2014–0053; Directorate Identifier 

2013–NM–174–AD. 

(a) Effective Date 

This AD is effective January 16, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200, –200LR, –300, –300ER, and 

777F series airplanes, certificated in any 

category, as identified in Boeing Service 

Bulletin 777–52A0050, Revision 1, dated 

August 7, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 52, Doors. 


rljohnson on DSK3VPTVN1PROD with RULES
73808 Federal Register / Vol. 79, No. 239 / Friday, December 12, 2014 / Rules and Regulations 

(e) Unsafe Condition 

This AD was prompted by reports of 

corroded, migrated, or broken spring pins of 

the girt bar floor fitting; in one case the 

broken pins prevented a door escape slide 

from deploying during a maintenance test. 

We are issuing this AD to prevent broken or 

migrated spring pins of the girt bar floor 

fittings, which could result in improper 

deployment of the escape slide/raft and 

consequent delay and injury during 

evacuation of passengers and crew from the 

cabin in the event of an emergency. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Spring Pin Replacement 

Within 37 months after the effective date 

of this AD: Replace the spring pin at both girt 

bar floor fittings at each passenger entry door 

with a new spring pin, in accordance with 

the Accomplishment Instructions of Boeing 

Service Bulletin 777–52A0050, Revision 1, 

dated August 7, 2014. 

(h) Credit for Previous Actions 

This paragraph provides credit for the 

action specified in paragraph (g) of this AD, 

if that action was performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 777–52A0050, dated June 

18, 2013, which is not incorporated by 

reference in this AD. 

(i) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install a spring pin having part 

number MS39086–261 or MS16562–252 at a 

girt bar floor fitting at a passenger entry door 

on any airplane. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (k)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane. 

(k) Related Information 

(1) For more information about this AD, 

contact Ana Martinez Hueto, Aerospace 

Engineer, Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6592; fax: 425–917–6591; 

email: ana.m.hueto@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses in paragraphs (l)(3) 

and (l)(4) of this AD. 

(l) 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. 

(i) Boeing Service Bulletin 777–52A0050, 

Revision 1, dated August 7, 2014. 

(ii) Reserved. 

(3) 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. 

(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, WA, on November 28, 

2014. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–28916 Filed 12–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1029; Directorate 

Identifier 2013–NM–177–AD; Amendment 

39–18042; AD 2014–25–01] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2010–13– 

04 for certain Bombardier, Inc. Model 

DHC–8–400 series airplanes. AD 2010– 

13–04 required modifying the nose 

landing gear (NLG) trailing arm. This 

new AD requires installing a new pivot 

pin retention mechanism. This new AD 

also adds airplanes to the applicability. 

This AD was prompted by a report of 

several missing or damaged pivot pin 

retention bolts. We are issuing this AD 

to prevent failure of the pivot pin 

retention bolt, which could result in a 

loss of directional control or loss of a 

NLG tire during take-off or landing. 

DATES: This AD becomes effective 

January 16, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 16, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of July 28, 2010 (75 FR 

35622, June 23, 2010). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-1029; 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., QSeries 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: 

Ricardo Garcia, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7331; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2010–13–04, 

Amendment 39–16335 (75 FR 35622, 

June 23, 2010). AD 2010–13–04 applied 

to certain Bombardier, Inc. Model DHC– 

8–400 series airplanes. The NPRM 

published in the Federal Register on 

December 24, 2013 (78 FR 77615). 


rljohnson on DSK3VPTVN1PROD with RULES