43744 Federal Register / Vol. 83, No. 167 / Tuesday, August 28, 2018 / Rules and Regulations 

this AD to require engine modification to 

prevent asymmetric thrust. The unsafe 

condition, if not addressed, could result in 

failure of the beta switch, loss of engine 

thrust control, and reduced control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Within 25 flight hours, 20 flight cycles, or 

30 days, whichever occurs first after the 

effective date of this AD, inspect and adjust 

the engine push-pull control, P/N M601– 

76.3, and replace beta switch, P/N P–S–2, 

with beta switch, P/N P–S–2A, in accordance 

with paragraphs 1.6. and 1.7. of GE Aviation 

Czech Service Bulletin (SB) SB–H80–76–00– 

00–0036, Revision No. 02, dated March 29, 

2018. 

(h) Installation Prohibition 

After the effective date of this AD: 

(1) Do not install beta switch, P/N P–S–2, 

on any engine. 

(2) Do not install a GE Aviation Czech 

H80–200 turboprop engine on any airplane 

unless the required actions in paragraph (g) 

of this AD have been complied with. This 

engine installation prohibition does not 

apply to an engine removal and subsequent 

re-installation on the same airplane during an 

airplane maintenance visit. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO Branch, 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 certification office, 

send it to the attention of the person 

identified in paragraph (j)(1) of this AD. You 

may email your request to: ANE-AD-AMOC@

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. 

(j) Related Information 

(1) For more information about this AD, 

contact Wego Wang, Aerospace Engineer, 

ECO Branch, FAA, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7134; fax: 781–238–7199; email: wego.wang@

faa.gov. 

(2) Refer to European Aviation Safety 

Agency AD 2018–0075, dated April 5, 2018, 

for more information. You may examine the 

European Aviation Safety Agency AD in the 

AD docket on the internet at http://

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2018–0723. 

(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) GE Aviation Czech Service Bulletin SB– 

H80–76–00–00–0036, Revision No. 02, dated 

March 29, 2018. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact GE Aviation Czech s.r.o., 

Beranovy ́ch 65, 199 02 Praha 9—Letnˇ any, 

Czech Republic; phone: +420 222 538 111; 

fax: +420 222 538 222. 

(4) You may view this service information 

at FAA, Engine & Propeller Standards 

Branch, 1200 District Avenue, Burlington, 

MA 01803. For information on the 

availability of this material at the FAA, call 

781–238–7759. 

(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 Burlington, Massachusetts, on 

August 21, 2018. 

Karen M. Grant, 

Acting Manager, Engine and Propeller 

Standards Branch, Aircraft Certification 

Service. 

[FR Doc. 2018–18575 Filed 8–27–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0554; Product 

Identifier 2016–NM–201–AD; Amendment 

39–19370; AD 2018–17–16] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus SAS Model A300 series 

airplanes; Model A300 B4–600, B4– 

600R, and F4–600R series airplanes, and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes); and Model 

A310 series airplanes. This AD was 

prompted by a static analysis performed 

by Airbus SAS that revealed some areas 

of the wing structure cannot sustain the 

damage limits previously published in 

certain structural repair manuals. This 

AD requires an inspection to determine 

whether repair or damage to certain 

wing areas is beyond the allowable 

limits; and repair if necessary. We are 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective October 2, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publication listed in this AD 

as of October 2, 2018. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus SAS, Airworthiness Office— 

EAW, Rond-Point Emile Dewoitine No: 

2, 31700 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 

61 93 44 51; email account.airwortheas@airbus.com; internet http://

www.airbus.com. You may view this 

service information at the FAA, 

Transport Standards Branch, 2200 

South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

It is also available on the internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2017– 

0554. 

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–2017– 

0554; or in person at Docket Operations 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this final rule, 

the regulatory evaluation, any 

comments received, and other 

information. The address for Docket 

Operations (phone: 800–647–5527) is 

Docket Operations, 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: Dan 

Rodina, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3225. 

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 all Airbus SAS Model A300 

series airplanes; Model A300 B4–600, 

B4–600R, and F4–600R series airplanes, 

and Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes); and Model 

A310 series airplanes. The NPRM 

published in the Federal Register on 

June 12, 2017 (82 FR 26869). 


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Federal Register / Vol. 83, No. 167 / Tuesday, August 28, 2018 / Rules and Regulations 43745 

We are issuing this AD to address any 

repair or damage on the wing structure 

that is outside the allowable structural 

limits. Such conditions could reduce 

the structural integrity of the wings and 

could result in loss of control of the 

airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2016–0229, 

dated November 15, 2016 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus SAS Model A300 series 

airplanes; Model A300 B4–600, B4– 

600R, and F4–600R series airplanes, and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes); and Model 

A310 series airplanes. The MCAI states: 

A static analysis performed by Airbus on 

A300, A310, A300–600, and A300–600ST 

aeroplanes, revealed that some areas of the 

wing structure cannot sustain the damage 

previously published in the A300, A310, 

A300–600, and A300–600ST Structural 

Repair Manuals (SRM). 

The SRMs were therefore amended to 

reduce the dimensions of allowable damage 

and to indicate the areas of the wing 

structure where damage is no longer 

acceptable. 

This condition, if not detected, could 

reduce the structural integrity of the wings. 

Consequently, Airbus issued Service 

Bulletins (SB) A300–57–0256, A310–57– 

2102, A300–57–6114, and A300–57–9027 

(hereafter referred to as ‘‘the applicable 

Airbus SB’’), as applicable for A300, A310, 

A300–600, and A300–600ST aeroplanes, to 

inspect the areas identified in these SBs and 

determine if the repair(s) or damage(s) found 

stay within the limits indicated in the latest 

SRM issue (including temporary revisions). 

For the reason described above, this 

[EASA] AD requires accomplishment of an 

inspection of the aeroplane records. If 

aeroplane records are missing or incomplete, 

a Detail Inspection (DET) of specific wing 

areas is required to ensure that no repair or 

damage is beyond the limits allowed in the 

current revision of the SRM (including 

temporary revisions) [and repair if 

necessary]. 

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–2017– 

0554. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. FedEx stated 

that it supported the NPRM. 

Request To Delay the Issuance Pending 

New Service Information 

Airbus and United Parcel Service 

(UPS) requested that we delay issuance 

of the final rule until new service 

information is released. Airbus stated 

that a configuration issue and an 

allowable damage limit issue has been 

identified for certain freighter 

manufacturer serial numbers, as 

specified in Airbus Service Bulletin 

A300–57–6114, Revision 00, dated 

August 3, 2015. Airbus also stated that 

it intends to update the service 

information. 

UPS stated that certain configurations 

specified in Airbus Service Bulletin 

A300–57–6114, Revision 00, dated 

August 3, 2015, do not meet the intent 

of the proposed AD because airplanes 

with a freighter configuration have an 

additional inspection of the wing lower 

skin between ribs 26 and 27. UPS also 

stated that the allowable damage 

limitations are inconsistent between 

Airbus Service Bulletin A300–57–6114, 

Revision 00, dated August 3, 2015, and 

applicable SRM references. 

We agree with the commenters’ 

request. Since the NPRM has been 

issued, Airbus SAS has issued Service 

Bulletin A300–57–6114, Revision 01, 

dated June 19, 2018, and has updated 

the applicable SRMs referenced in the 

service information. Airbus Service 

Bulletin A300–57–6114, Revision 01, 

dated June 19, 2018, does not contain 

substantive changes. Therefore, we have 

revised paragraph (i)(2) of this AD to 

refer to Airbus Service Bulletin A300– 

57–6114, Revision 01, dated June 19, 

2018. We have also added paragraph (j) 

of this AD to give credit for actions in 

paragraph (g) of this AD completed 

before the effective date of this AD using 

Airbus Service Bulletin A300–57–6114, 

Revision 00, dated August 3, 2015. We 

redesignated subsequent paragraphs 

accordingly. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this 

final rule 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 

addressing 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 final rule. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following Airbus 

SAS Service Information. 

• Airbus Service Bulletin A300–57– 

0256, Revision 00, dated August 3, 2015 

(Airbus Model A300 series airplanes). 

• Airbus Service Bulletin A300–57– 

6114, Revision 01, dated June 19, 2018 

(for Model A300 B4–600, B4–600R, and 

F4–600R series airplanes, and Model 

A300 C4–605R Variant F airplanes 

(collectively called Model A300–600 

series airplanes)). 

• Airbus Service Bulletin A310–57– 

2102, Revision 00, dated August 3, 2015 

(for Model A310 series airplanes). 

This service information describes a 

review of the airplane maintenance 

records and a detailed inspection of the 

left-hand and right-hand wing areas to 

determine whether any repair or damage 

is beyond the allowable limits in the 

current revision of the SRM, and repair 

if necessary. These documents are 

distinct since they apply to different 

airplane models in different 

configurations. 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 128 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection ...................... Up to 18 work-hours × $85 per hour = $1,530 .. $0 Up to $1,530 ................ Up to $195,840. 


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43746 Federal Register / Vol. 83, No. 167 / Tuesday, August 28, 2018 / Rules and Regulations 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

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. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to transport category 

airplanes and associated appliances to 

the Director of the System Oversight 

Division. 

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 

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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2018–17–16 Airbus SAS: Amendment 39– 

19370; Docket No. FAA–2017–0554; 

Product Identifier 2016–NM–201–AD. 

(a) Effective Date 

This AD is effective October 2, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus SAS Model 

A300 B2–1A, B2–1C, B2K–3C, B2–203, B4– 

2C, B4–103, and B4–203 airplanes; Model 

A300 B4–600, B4–600R, and F4–600R series 

airplanes, and Model A300 C4–605R Variant 

F airplanes (collectively called Model A300– 

600 series airplanes); and Model A310–203, 

–204, –221, –222, –304, –322, –324, and –325 

airplanes; certificated in any category, all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a static analysis 

performed by Airbus SAS that revealed that 

some areas of the wing structure cannot 

sustain the damage limits previously 

published in the Airbus A300, A310, A300– 

600, and A300–600ST Structural Repair 

Manuals. We are issuing this AD to detect 

and correct any repair or damage on the wing 

structure that is outside the allowable 

structural limits. Such conditions could 

reduce the structural integrity of the wings 

and could result in loss of control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Within 36 months after the effective date 

of this AD: Do a detailed inspection of the 

left-hand and right-hand wing areas to 

determine whether any repair or damage 

exceeds the allowable structural limits, in 

accordance with the Accomplishment 

Instructions of the applicable service 

information specified in paragraph (i) of this 

AD. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if it can be positively determined 

from that review whether any repair or 

damage exceeds the allowable structural 

limits and the airplane configuration can be 

conclusively determined from that review. 

(h) Corrective Action 

If, during any review or inspection, as 

required by paragraph (g) of this AD, any 

repair or damage is found that is outside the 

allowable structural limits specified in the 

applicable service information in paragraph 

(i) of this AD: Within 3 months after 

accomplishing the review or inspection 

required by paragraph (g) of this AD, repair 

using a method approved by the Manager, 

International Section, Transport Standards 

Branch, FAA; or the European Aviation 

Safety Agency (EASA); or Airbus SAS’s 

EASA Design Organization Approval (DOA). 

If approved by the DOA, the approval must 

include the DOA-authorized signature. 

(i) Service Information for the Actions 

Specified in Paragraph (g) of This AD 

Use the applicable service information for 

the actions specified in paragraph (g) of this 

AD. 

(1) Airbus Service Bulletin A300–57–0256, 

Revision 00, dated August 3, 2015 (for Airbus 

Model A300 series airplanes). 

(2) Airbus Service Bulletin A300–57–6114, 

Revision 01, dated June 19, 2018 (for Model 

A300 B4–600, B4–600R, and F4–600R series 

airplanes, and Model A300 C4–605R Variant 

F airplanes (collectively called Model A300– 

600 series airplanes)). 

(3) Airbus Service Bulletin A310–57–2102, 

Revision 00, dated August 3, 2015 (for Model 

A310 series airplanes). 

(j) 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 Airbus Service Bulletin 

A300–57–6114, Revision 00, dated August 3, 

2015. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards Branch, 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 International 

Section, send it to the attention of the person 

identified in paragraph (l)(2) of this AD. 

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. 


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Federal Register / Vol. 83, No. 167 / Tuesday, August 28, 2018 / Rules and Regulations 43747 

(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 Section, 

Transport Standards Branch, FAA; or EASA; 

or Airbus SAS’s EASA DOA. If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

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 procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2016–0229, dated November 15, 2016, 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–2017–0554. 

(2) For more information about this AD, 

contact Dan Rodina, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 2200 South 216th St., Des 

Moines, WA 98198; telephone and fax 206– 

231–3225. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A300–57–0256, 

Revision 00, dated August 3, 2015. 

(ii) Airbus Service Bulletin A300–57–6114, 

Revision 01, dated June 19, 2018. 

(iii) Airbus Service Bulletin A310–57– 

2102, Revision 00, dated August 3, 2015. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, Rond-Point Emile Dewoitine 

No: 2, 31700 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; internet http://www.airbus.com. 

(4) You may view this service information 

at the FAA, Transport Standards Branch, 

2200 South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

(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 Des Moines, Washington, on 

August 16, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–18272 Filed 8–27–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0118; Product 

Identifier 2017–NM–083–AD; Amendment 

39–19371; AD 2018–17–17] 

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–8–400 

series airplanes. This AD was prompted 

by reports of arcing and smoke 

emanating from the windshields. This 

AD requires a revision to the 

maintenance or inspection program, as 

applicable, to include an inspection of 

the windshield moisture seal for signs of 

cracks, erosion, wear, and other 

deterioration; doing that inspection and 

repair if necessary; and re-torqueing the 

screws that fasten the windshield heater 

terminal lugs and applying sealant to 

the screw heads of the windshield 

heaters. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective October 2, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 2, 2018. 

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 Standards Branch, 

2200 South 216th St., Des Moines, WA. 

For information on the availability of 

this material at the FAA, call 206–231– 

3195. It is also available on the internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2018–0118. 

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–2018– 

0118; or in person at Docket Operations 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this final rule, 

the regulatory evaluation, any 

comments received, and other 

information. The address for Docket 

Operations (phone: 800–647–5527) is 

Docket Operations, 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: 

Steve Dzierzynski, Aerospace Engineer, 

Avionics and Administrative Services 

Section, FAA, New York ACO Branch, 

1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone 516– 

228–7367; 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–8–400 series airplanes. The NPRM 

published in the Federal Register on 

March 1, 2018 (83 FR 8810). The NPRM 

was prompted by reports of arcing and 

smoke emanating from the windshields. 

The NPRM proposed to require a 

revision to the maintenance or 

inspection program, as applicable, to 

include an inspection of the windshield 

moisture seal for signs of cracks, 

erosion, wear, and other deterioration; 

doing that inspection and repair if 

necessary; and re-torqueing the screws 

that fasten the windshield heater 

terminal lugs and applying sealant to 

the screw heads of the windshield 

heaters. 

We are issuing this AD to detect and 

correct loose windshield heater terminal 

lugs. Loose terminal lugs could create 

sparks that lead to burning of the lugs 

and, due to the excessive heat, cracking 

of the windshields. If not corrected, 

such a condition could cause a loss of 

cabin pressure resulting in an 

emergency descent. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian AD 


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