85118 Federal Register / Vol. 81, No. 227 / Friday, November 25, 2016 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2016–24–01 Bombardier, Inc.: Amendment 

39–18718; Docket No. FAA–2016–5044; 

Directorate Identifier 2014–NM–166–AD. 

(a) Effective Date 

This AD is effective December 30, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. 

airplanes identified in paragraphs (c)(1), 

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

any category, serial numbers 003 through 672 

inclusive, on which terminal block part 

number 82450075–001 is installed. 

(1) Model DHC–8–102, –103, and –106 

airplanes. 

(2) Model DHC–8–201 and –202 airplanes. 

(3) Model DHC–8–301, –311, and –315 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24, Electrical Power. 

(e) Reason 

This AD was prompted by a report of heat 

damage found on a nacelle firewall after an 

unsuccessful engine ground start and several 

events of heat damage found on direct 

current starter/generator terminal block 

assemblies. We are issuing this AD to prevent 

arcing between the firewall and terminal 

blocks that are missing insulating sleeves on 

the conductive bushings, which could, in 

combination with a fuel or hydraulic fluid 

leak, be an ignition source for a fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Corrective Action 

Within 2,500 flight cycles or 14 months 

after the effective date of this AD, whichever 

occurs first, perform a detailed visual 

inspection of the right-hand side and lefthand side nacelle firewalls and terminal 

block assemblies, as defined in Bombardier 

Service Bulletin 8–24–92, Revision A, dated 

April 11, 2014, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–24–92, Revision A, dated 

April 11, 2014. 

(1) If the inspection finds no damage on the 

engine firewalls and the terminal blocks, and 

that undamaged insulating sleeves are 

installed on both terminal blocks, no further 

action is required by this AD. 

(2) If the inspection finds that no insulating 

sleeves are installed, or the existing sleeves 

are damaged, and there is no damage to the 

nacelle firewall and terminal block, before 

further flight, install the replacement 

insulating sleeves, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–24–92, Revision A, dated 

April 11, 2014. 

(3) If the inspection finds that no insulating 

sleeves are installed, or any existing sleeve is 

damaged, and there is no damage to the 

nacelle firewall, but there is damage to the 

terminal block, before further flight, replace 

the terminal block assembly (which includes 

insulating sleeves), in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–24–92, Revision A, dated 

April 11, 2014. 

(4) If the inspection finds that no insulating 

sleeves are installed and there is damage to 

the nacelle firewall and the terminal block, 

repair the damage using a method approved 

by the Manager, New York Aircraft 

Certification Office (ACO), ANE–170, Engine 

and Propeller Directorate, FAA; or Transport 

Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). 

(h) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Bombardier Service 

Bulletin 8–24–92, dated September 25, 2013. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO, 

ANE–170, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. In 

accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

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. 

(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. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–03R1, 

dated July 24, 2014, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2016–5044. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(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 8–24–92, 

Revision A, dated April 11, 2014. 

(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 

November 10, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–28054 Filed 11–23–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–5041; Directorate 

Identifier 2015–NM–102–AD; Amendment 

39–18719; AD 2016–24–02] 

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 747–8 and 

747–8F series airplanes. This AD was 

prompted by a report that static strength 

analysis has shown that the aluminum 

transmission aft bearing plate 

assemblies have inadequate structural 

strength for one or more of the required 

load cases. This AD requires removing 

aluminum transmission aft bearing plate 

assemblies from the flap track and 

installing titanium transmission aft 

bearing plate assemblies to the flap 

track. We are issuing this AD to address 

the unsafe condition on these products. 


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Federal Register / Vol. 81, No. 227 / Friday, November 25, 2016 / Rules and Regulations 85119 

DATES: This AD is effective December 

30, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 30, 2016. 

ADDRESSES: For service information 

identified in this final rule, 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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

5041. 

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–2016– 

5041; 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: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6432; fax: 425– 

917–6590; email: bill.ashforth@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 747–8 and 747–8F series 

airplanes. The NPRM published in the 

Federal Register on April 5, 2016 (81 FR 

19514) (‘‘the NPRM’’). The NPRM was 

prompted by a report that static strength 

analysis has shown that the aluminum 

transmission aft bearing plate 

assemblies have inadequate structural 

strength for one or more of the required 

load cases, including cases for drive 

system jam, flap skew, and structural 

damage tolerance. Inadequate structural 

strength can result in damage to the 

transmission aft bearing plate 

assemblies. The NPRM proposed to 

require removing aluminum 

transmission aft bearing plate 

assemblies from the flap track and 

installing titanium transmission aft 

bearing plate assemblies to the flap 

track. We are issuing this AD to prevent 

inadequate structural strength of 

transmission aft bearing plate 

assemblies. This condition could result 

in damaged transmission aft bearing 

plate assemblies, which could result in 

incorrect operation and departure of the 

flap from the airplane and consequent 

loss of controllability of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Use the Latest Service 

Information 

Boeing requested that we revise the 

NPRM to refer to Boeing Alert Service 

Bulletin 747–57A2348, Revision 1, 

dated February 26, 2016. Boeing stated 

that Boeing Alert Service Bulletin 747– 

57A2348, dated June 12, 2015, 

erroneously included three airplanes, 

line numbers 1435, 1506, and 1509, 

which were delivered with the 

terminating action already incorporated. 

Boeing stated that the airplane 

effectivity in paragraph 1.A.1. of Boeing 

Alert Service Bulletin 747–57A2348, 

Revision 1, dated February 26, 2016, is 

listed correctly; however, airplane line 

numbers 1435, 1506, and 1509 were still 

erroneously included in the table that 

lists the airplane groups by line 

numbers. Boeing noted that Boeing 

Alert Service Bulletin 747–57A2348, 

Revision 1, dated February 26, 2016, 

also contains corrections to the access 

requirements, part quantities, and part 

numbers. 

We agree with the commenter’s 

request for the reasons provided. We 

have updated this final rule accordingly. 

Since the table in paragraph 1.A.1. of 

Boeing Alert Service Bulletin 747– 

57A2348, Revision 1, dated February 26, 

2016, is not accurate, we have also 

revised paragraph (c) of this AD to state 

that the AD is applicable to Model 747– 

8 and 747–8F series airplanes, except 

for line numbers 1435, 1506, and 1509, 

which were delivered with the 

terminating action already incorporated. 

We have also added a new paragraph (h) 

to this AD, which provides credit for 

actions completed before the effective 

date of this AD using Boeing Alert 

Service Bulletin 747–57A2348, dated 

June 12, 2015. We have redesignated 

subsequent paragraphs accordingly. 

Request To Revise the Costs of 

Compliance 

Boeing requested that we update the 

Costs of Compliance section of the 

NPRM with the latest information in 

Boeing Alert Service Bulletin 747– 

57A2348, Revision 1, dated February 26, 

2016. Boeing stated that the work hours 

and parts costs have been updated with 

the new service information. 

We agree with the commenter’s 

request for the reason provided. We 

have updated this final rule accordingly. 

Request for Credit for Previous Actions 

Boeing requested that we add a 

statement to the NPRM to indicate that 

no further work is required on airplanes 

that have completed the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–57A2348, 

dated June 12, 2015. Boeing stated that 

Boeing Alert Service Bulletin 747– 

57A2348, Revision 1, dated February 26, 

2016, has no effect on airplanes that 

have incorporated Boeing Alert Service 

Bulletin 747–57A2348, dated June 12, 

2015. 

We agree with the commenter’s 

request for the reason provided. As 

stated previously, we have revised this 

AD to provide credit for actions 

completed before the effective date of 

this AD using Boeing Alert Service 

Bulletin 747–57A2348, dated June 12, 

2015. 

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 for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 747–57A2348, Revision 1, 

dated February 26, 2016. The service 

information describes procedures for 

removing the aluminum transmission 

aft bearing plate assembly from the flap 


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85120 Federal Register / Vol. 81, No. 227 / Friday, November 25, 2016 / Rules and Regulations 

track and installing a new titanium 

transmission aft bearing plate assembly 

to the flap track. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 11 

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 .................................................... 136 work-hours × $85 per hour = $11,560 ... $43,787 $55,347 $608,817 

According to the manufacturer, all 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, 

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): 

2016–24–02 The Boeing Company: 

Amendment 39–18719; Docket No. 

FAA–2016–5041; Directorate Identifier 

2015–NM–102–AD. 

(a) Effective Date 

This AD is effective December 30, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–8 and 747–8F series airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin 747–57A2348, 

Revision 1, dated February 26, 2016; except 

for line numbers 1435, 1506, and 1509, 

which were delivered with the terminating 

action already incorporated and are not 

affected by this AD. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a report that 

static strength analysis has shown that the 

aluminum transmission aft bearing plate 

assemblies have inadequate structural 

strength for one or more of the required load 

cases, including cases for drive system jam, 

flap skew, and structural damage tolerance. 

Inadequate structural strength can result in 

damage to the transmission aft bearing plate 

assemblies. We are issuing this AD to prevent 

inadequate structural strength of 

transmission aft bearing plate assemblies. 

This condition could result in damaged 

transmission aft bearing plate assemblies, 

which could result in incorrect operation and 

departure of the flap from the airplane and 

consequent loss of controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement 

Within 48 months after the effective date 

of this AD: Remove aluminum transmission 

aft bearing plate assemblies from the flap 

track and install new titanium transmission 

aft bearing plate assemblies to the flap track, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–57A2348, Revision 1, dated February 26, 

2016. 

(h) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 747–57A2348, dated June 

12, 2015. 

(i) 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 (j)(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, 

modification, or alteration required by this 


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Federal Register / Vol. 81, No. 227 / Friday, November 25, 2016 / Rules and Regulations 85121 

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. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (i)(4)(i) and (i)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. An AMOC is required for any 

deviations to RC steps, including substeps 

and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(j) Related Information 

(1) For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6432; fax: 425– 

917–6590; email: bill.ashforth@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(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 the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 747– 

57A2348, Revision 1, dated February 26, 

2016. 

(ii) Reserved. 

(3) For Boeing 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 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. 

(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/ibr-locations.html. 

Issued in Renton, Washington, on 

November 10, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–28059 Filed 11–23–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–7427; Directorate 

Identifier 2016–NM–041–AD; Amendment 

39–18714; AD 2016–23–07] 

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) 2013–02– 

08 for all Bombardier, Inc. Model CL– 

600–2B19 (Regional Jet Series 100 & 

440) airplanes. AD 2013–02–08 required 

inspection of the trunnions and upper 

and lower pins of the horizontal 

stabilizer trim actuator (HSTA), and 

replacement or re-identification if 

necessary; and revision of the 

maintenance program to include safe 

life limits and inspection requirements 

for the HSTA. This new AD requires 

certain actions related to the trunnions 

and pins for the HSTA, revising the 

maintenance or inspection program, and 

removing certain airplanes from the 

applicability. This AD was prompted by 

a determination that not all affected 

attachment pins and trunnions were 

included in the inspections required by 

AD 2016–02–08, and that incorrect 

attachment hardware may have been 

used in replacements on certain 

airplanes. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective December 

30, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 30, 2016. 

ADDRESSES: For service information 

identified in this final rule, 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

7427. 

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–2016– 

7427; 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 (telephone 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: 

Cesar Gomez, 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) 228–7318; 

fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2013–02–08, 

Amendment 39–17329 (78 FR 7647, 

February 4, 2013) (‘‘AD 2013–02–08’’). 

AD 2013–02–08 applied to all 

Bombardier, Inc. Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. The NPRM published in the 

Federal Register on July 15, 2016 (81 FR 

45992). The NPRM was prompted by a 

determination that not all affected 

attachment pins and trunnions were 

included in the required inspections. In 

addition, for certain airplanes on which 

the replacement in AD 2013–02–08 was 

done, incorrect attachment hardware 

may have been used. The NPRM 

proposed to require measuring the 

diameter of certain bolts and attach 

holes, and, as applicable, measuring the 

diameter of the attach holes in the 

trunnions and pins; doing detailed 

visual inspections of the trunnions, 

pins, and spacers; doing corrective 

actions; and re-identifying trunnions 

and pins. The NPRM also proposed to 


ehiers on DSK5VPTVN1PROD with RULES