31648 Federal Register / Vol. 83, No. 131 / Monday, July 9, 2018 / Rules and Regulations 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Functional Test 

Within 42 months after the effective date 

of this AD, do a trim tank overflow functional 

test in accordance with the Accomplishment 

Instructions of the service information 

specified in paragraphs (g)(1) through (g)(3), 

as applicable. 

(1) Airbus Service Bulletin A330–28–3130, 

Revision 00, dated May 18, 2017. 

(2) Airbus Service Bulletin A340–28–4140, 

Revision 00, dated May 18, 2017. 

(3) Airbus Service Bulletin A340–28–5061, 

Revision 00, dated May 18, 2017. 

(h) Corrective Actions 

(1) If, during the functional test required by 

paragraph (g) of this AD, the trim tank 

maximum allowable pressure is exceeded: 

Before further flight, contact the Manager, 

International Section, Transport Standards 

Branch, FAA; or the European Aviation 

Safety Agency (EASA); or Airbus’s EASA 

Design Organization Approval (DOA) to 

obtain instructions for corrective actions, and 

within the compliance time indicated in 

those instructions accomplish the corrective 

actions accordingly. 

(2) If, during the functional test required by 

paragraph (g) of this AD, the trim surge tank 

maximum allowable pressure is exceeded: 

Before further flight, do a general visual 

inspection of the aperture leading to the 

flame arrestors (NACA duct) and do a 

detailed inspection of the flame arrestor in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

28–3130, Revision 00, dated May 18, 2017; 

Airbus Service Bulletin A340–28–4140, 

Revision 00, dated May 18, 2017; or Airbus 

Service Bulletin A340–28–5061, Revision 00, 

dated May 18, 2017; as applicable. 

(3) If, during any inspection required by 

paragraph (h)(2) of this AD, any discrepancy 

(blockage or damage of the NACA duct) is 

found: Before further flight, accomplish the 

applicable corrective actions in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A330–28–3130, 

Revision 00, dated May 18, 2017; Airbus 

Service Bulletin A340–28–4140, Revision 00, 

dated May 18, 2017; or Airbus Service 

Bulletin A340–28–5061, Revision 00, dated 

May 18, 2017; as applicable. 

(i) 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 International Section, send it 

to the attention of the person identified in 

paragraph (j)(2) of this AD. Information may 

be emailed to: 9-ANM-116-AMOCREQUESTS@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. 

(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’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized 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. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0152, dated August 17, 2017, 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–2018–0270. 

(2) For more information about this AD, 

contact Vladimir Ulyanov, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax 206–231–3229. 

(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) Airbus Service Bulletin A330–28–3130, 

Revision 00, dated May 18, 2017. 

(ii) Airbus Service Bulletin A340–28–4140, 

Revision 00, dated May 18, 2017. 

(iii) Airbus Service Bulletin A340–28– 

5061, Revision 00, dated May 18, 2017. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, Rond-Point Emile Dewoitine 

No: 2, 31700 Blagnac Cedex, France; 

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

93 45 80; email airworthiness.A330-A340@

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 June 

26, 2018. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2018–14504 Filed 7–6–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0274; Product 

Identifier 2017–NM–128–AD; Amendment 

39–19325; AD 2018–14–05] 

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 BD–100–1A10 

airplanes. This AD was prompted by 

reports of fire incidents of the auxiliary 

power unit (APU) inlet, which caused 

tail cone damage after an initial failed 

APU start followed by two or more inflight APU start attempts. This AD 

requires modification of the APU 

electronic control unit (ECU) wiring 

harness. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective August 13, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 13, 2018. 

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 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– 

0274. 


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Federal Register / Vol. 83, No. 131 / Monday, July 9, 2018 / Rules and Regulations 31649 

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– 

0274; 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 in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Assata Dessaline, Aerospace Engineer, 

Avionics and Administrative Services 

Section, FAA, New York ACO Branch, 

1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone 516– 

228–7301; fax 516–794–5531; email 9- 

avs-nyaco-cos@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 Bombardier, Inc., Model 

BD–100–1A10 airplanes. The NPRM 

published in the Federal Register on 

April 13, 2018 (83 FR 16013). The 

NPRM was prompted by reports of fire 

incidents of the APU inlet, which 

caused tail cone damage after an initial 

failed APU start followed by two or 

more in-flight APU start attempts. The 

NPRM proposed to require modification 

of the APU ECU wiring harness. 

We are issuing this AD to address 

failure of the APU inlet, which could 

result in a fire during flight. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2017–26, 

dated July 31, 2017, (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc., Model BD– 

100–1A10 airplanes. The MCAI states: 

APU inlet fire incidents causing tail cone 

damage have been reported after an initial 

failed APU start followed by two or more inflight APU start attempts. Bombardier, Inc. 

(BA) has determined that the in-flight 

negative pressure differential at the APU 

inlet allows flash fires of residual fuel in the 

APU combustor to exit through the APU 

inlet. 

As an interim mitigating action, BA has 

revised the affected aeroplane Aircraft Flight 

Manual (AFM) procedure for in-flight APU 

start to limit the number of APU start 

attempts. 

To further address the safety concerns 

associated with in-flight APU inlet fire, BA 

is introducing a modification to the APU 

Electronic Control Unit (ECU) wiring harness 

that will prevent a second attempt to start the 

APU following a failed start in flight. This 

[Canadian] AD is issued to mandate 

compliance with BA Service Bulletin (SB) 

100–49–04 or SB 350–49–001, as applicable, 

on affected aeroplanes. 

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–2018– 

0274. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

We received no comments on the NPRM 

or on the determination of the cost to 

the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this 

final rule 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 

addressing 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 

Bombardier has issued Service 

Bulletin 100–49–04, dated March 29, 

2017; and Service Bulletin 350–49–001, 

dated March 29, 2017. This service 

information describes a modification of 

the APU ECU harness. 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 198 

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 

Modification ............................. 3 work-hours × $85 per hour = $255 ..................................... $120 $375 $74,250 

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 


sradovich on DSK3GMQ082PROD with RULES
31650 Federal Register / Vol. 83, No. 131 / Monday, July 9, 2018 / Rules and Regulations 

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): 

2018–14–05 Bombardier, Inc.: Amendment 

39–19325; Docket No. FAA–2018–0274; 

Product Identifier 2017–NM–128–AD. 

(a) Effective Date 

This AD is effective August 13, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc., 

Model BD–100–1A10 airplanes, certificated 

in any category, serial numbers (S/Ns) 20003 

through 20500 inclusive and 20501 through 

20696 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 49, Airborne auxiliary power. 

(e) Reason 

This AD was prompted by reports of fire 

incidents of the auxiliary power unit (APU) 

inlet, which caused tail cone damage after an 

initial failed APU start followed by two or 

more in-flight APU start attempts. We are 

issuing this AD to prevent failure of the APU 

inlet, which could result in a fire during 

flight. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

Within 30 months after the effective date 

of this AD: Modify the APU electronic 

control unit (ECU) wiring harness, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

100–49–04, dated March 29, 2017 (for S/N 

20003 through 20500 inclusive); or 

Bombardier Service Bulletin 350–49–001, 

dated March 29, 2017 (for S/N 20501 through 

20696 inclusive). 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO 

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 ATTN: Program Manager, 

Continuing Operational Safety, FAA, New 

York ACO Branch, 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 Branch, 

FAA; or Transport Canada Civil Aviation 

(TCCA); or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(i) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2017–26, dated 

July 31, 2017, 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– 

2018–0274. 

(2) For more information about this AD, 

contact Assata Dessaline, Aerospace 

Engineer, Avionics and Administrative 

Services Section, New York ACO Branch, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone 516–228– 

7301; fax 516–794–5531; email 9-avs-nyacocos@faa.gov. 

(j) 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 100–49–04, 

dated March 29, 2017. 

(ii) Bombardier Service Bulletin 350–49– 

001, dated March 29, 2017. 

(3) For Bombardier, Inc. service 

information identified in this AD, 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. 

(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 June 

26, 2018. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2018–14500 Filed 7–6–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0115; Product 

Identifier 2017–NM–110–AD; Amendment 

39–19322; AD 2018–14–02] 

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 777–200, 

–200LR, –300, and –300ER series 

airplanes. This AD was prompted by 

reports that additional areas of Boeing 

Material Specification (BMS) 8–39 

flexible urethane foam were found 

during a routine inspection. This AD 

requires an inspection for foam 

insulation on the dripshield above the 

overhead panel support structure and 

replacement if necessary. For certain 

airplanes, this AD also requires 

replacement of foam insulation on the 

overhead panel support structure. We 

are issuing this AD to address the unsafe 

condition on these products. 


sradovich on DSK3GMQ082PROD with RULES