85116 Federal Register / Vol. 81, No. 227 / Friday, November 25, 2016 / Rules and Regulations 

Original Issue, refers to airplanes with 

specified total flight-cycles ‘‘at the original 

issue date of this service bulletin.’’ This AD, 

however, applies to the airplanes with the 

specified total flight-cycles as of the effective 

date of this AD. 

(3) If any cracking is found during any 

inspection required by this AD, and ASB 

737–53A1347 Original Issue specifies to 

contact Boeing for appropriate action: Before 

further flight, repair the cracking or replace 

the stub beam, using a method approved in 

accordance with the procedures specified in 

paragraph (l) of this AD. 

(k) No Economic Inspection Required 

This AD does not require the 

‘‘Recommended Economic Inspection’’ 

specified in paragraph 3.B.3. of the 

Accomplishment Instructions of ASB 737– 

53A1347 Original Issue. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 (m) of this AD. Information may be 

emailed to: 9-ANM-LAACO-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 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

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) Except as required by paragraph (j)(3) 

of this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (l)(4)(i) and (l)(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. 

(m) Related Information 

For more information about this AD, 

contact Galib Abumeri, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office (ACO), 

3960 Paramount Boulevard, Lakewood, CA 

90712–4137; phone: 562–627–5324; fax: 562– 

627–5210; email: galib.abumeri@faa.gov. 

(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 the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 737– 

53A1347, Original Issue, dated December 9, 

2015. 

(ii) Reserved. 

(3) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: 

Contractual & Data Services (C&DS), 2600 

Westminster Blvd., MC 110–SK57, Seal 

Beach, CA 90740–5600; telephone 562–797– 

1717; 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, Washington, on 

November 8, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–27640 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–2016–5044; Directorate 

Identifier 2014–NM–166–AD; Amendment 

39–18718; AD 2016–24–01] 

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, and –106 airplanes; and Model 

DHC–8–200 and –300 series airplanes. 

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. This AD 

requires an inspection to detect damage 

on the nacelle firewalls and the terminal 

block assemblies and to make sure the 

insulating sleeves are installed and have 

no damage, and corrective action if 

necessary. 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 a certain publication listed in this AD 

as of December 30, 2016. 

ADDRESSES: For service information 

identified in this final rule, 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

5044. 

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– 

5044; 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 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: 

Assata Dessaline, Aerospace Engineer, 

Avionics and Flight Test Branch, ANE– 

172, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 


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Federal Register / Vol. 81, No. 227 / Friday, November 25, 2016 / Rules and Regulations 85117 

11590; telephone 516–228–7301; 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, and –106 airplanes; 

and Model DHC–8–200 and –300 series 

airplanes. The NPRM published in the 

Federal Register on April 12, 2016 (81 

FR 21495) (‘‘the NPRM’’). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–03R1, 

dated July 24, 2014 (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, and –106 airplanes; 

and Model DHC–8–200 and –300 series 

airplanes. The MCAI states: 

There has been one in-service report of 

heat damage on a nacelle firewall found after 

an unsuccessful engine ground start. There 

have also been several reports of heat damage 

found on Direct Current Starter/Generator 

terminal block assemblies, part number (P/N) 

82450075–001. 

The investigation determined that in all 

cases, the heat damage was caused by arcing 

between the firewall and terminal blocks 

with missing insulating sleeves on the 

conductive bushings. The insulating sleeves 

may have been inadvertently omitted during 

the incorporation of Modsum 8/1926, or 

during the installation of terminal blocks P/ 

N 82450075–001. 

Arcing with the firewall becomes an 

ignition source, creating a potential fire 

hazard when combined with a fuel or 

hydraulic fluid leak. 

The original issue of this [Canadian] AD 

mandated the [detailed visual] inspection [for 

damage to the nacelle firewalls and to make 

sure the insulating sleeves are installed and 

have no damage] and rectification [corrective 

actions such as installing or replacing 

insulating sleeves, or replacing a terminal 

block], as required, of the nacelle firewall 

and terminal block assembly P/N 82450075– 

001 installed with Modsum 8/1926. 

Revision 1 of this [Canadian] AD is issued 

to revise the Applicability to ensure that the 

terminal blocks have the insulating sleeves 

installed. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

5044. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM and the FAA’s 

response to the comment. 

Request To Reduce the Compliance 

Time 

The Air Line Pilots Association, 

International requested that, due to the 

nature of the AD, the proposed 14- 

month compliance time be reduced to 

10 months. 

We do not agree to reduce the 

compliance time. The 14-month 

compliance time was developed by 

TCCA in coordination with Bombardier, 

Inc., and we concur that it is an 

appropriate compliance time. However, 

if we receive data to justify a shorter 

compliance time, we may consider 

further rulemaking on this issue. We 

have not changed this AD in this regard. 

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 for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Bombardier Service 

Bulletin 8–24–92, Revision A, dated 

April 11, 2014. The service information 

describes procedures for an inspection 

to detect damage on the nacelle 

firewalls and the terminal block 

assemblies and to make sure the 

insulating sleeves are installed and have 

no damage, and corrective action. 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 75 

airplanes of U.S. registry. 

We also estimate that it will take 

about 2 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $12,750, or $170 per 

product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 1 work-hour and require parts 

costing $551, for a cost of $636 per 

product. We have no way of 

determining the number of aircraft that 

might need these actions. 

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. 

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. 


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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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