Federal Register / Vol. 83, No. 237 / Tuesday, December 11, 2018 / Rules and Regulations 63561 

more engines, loss of thrust control, and loss 

of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Within 60 days after the effective date 

of this AD, remove electronic engine control 

(EEC) system operation (OPS) software, P/N 

2628M86P10 or earlier; and engine health 

monitoring (EHM) software, P/N 

2628M87P10 or earlier, from the engine and 

from service. 

(2) Before further flight after the removal of 

the EEC OPS and EHM software required by 

paragraph (g)(1) of this AD, install EEC OPS 

and EHM software that is eligible for 

installation. 

(h) Installation Prohibition 

After 60 days from the effective date of this 

AD, do not operate any engine identified in 

paragraph (c) of this AD with EEC OPS 

software, P/N 2628M86P10 or earlier, 

installed; or EHM software, P/N 2628M87P10 

or earlier, installed. 

(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) 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 

For more information about this AD, 

contact Christopher McGuire, Aerospace 

Engineer, ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 781– 

238–7120; fax: 781–238–7199; email: 

chris.mcguire@faa.gov. 

(k) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

December 3, 2018. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2018–26611 Filed 12–10–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0960; Product 

Identifier 2018–NM–151–AD; Amendment 

39–19512; AD 2018–23–51] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

Editorial Note: Rule document 2018–26365 

was originally published on pages 62697 

through 62700 in the issue of Thursday, 

December 6, 2018. In that publication, on 

page 62700, in Figure 2 to paragraph (h), the 

last sentence in the table was inadvertently 

truncated. The corrected document is 

published here in its entirety. 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 737–8 and –9 

airplanes. This emergency AD was sent 

previously to all known U.S. owners 

and operators of these airplanes. This 

AD requires revising certificate 

limitations and operating procedures of 

the airplane flight manual (AFM) to 

provide the flight crew with runaway 

horizontal stabilizer trim procedures to 

follow under certain conditions. This 

AD was prompted by analysis 

performed by the manufacturer showing 

that if an erroneously high single angle 

of attack (AOA) sensor input is received 

by the flight control system, there is a 

potential for repeated nose-down trim 

commands of the horizontal stabilizer. 

We are issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective December 

21, 2018 to all persons except those 

persons to whom it was made 

immediately effective by Emergency AD 

2018–23–51, issued on November 7, 

2018, which contained the requirements 

of this amendment. 

We must receive comments on this 

AD by January 22, 2019. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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– 

0960; 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 street 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: 

Douglas Tsuji, Senior Aerospace 

Engineer, Systems and Equipment 

Section, FAA, Seattle ACO Branch, 2200 

South 216th St., Des Moines, WA 98198; 

phone and fax: 206–231–3548; email: 

Douglas.Tsuji@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On November 7, 2018, we issued 

Emergency AD 2018–23–51, which 

requires revising certificate limitations 

and operating procedures of the AFM to 

provide the flight crew with runaway 

horizontal stabilizer trim procedures to 

follow under certain conditions. This 

emergency AD was sent previously to 

all known U.S. owners and operators of 

these airplanes. This action was 

prompted by analysis performed by the 

manufacturer showing that if an 

erroneously high single AOA sensor 

input is received by the flight control 

system, there is a potential for repeated 

nose-down trim commands of the 

horizontal stabilizer. This condition, if 

not addressed, could cause the flight 

crew to have difficulty controlling the 

airplane, and lead to excessive nosedown attitude, significant altitude loss, 

and possible impact with terrain. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD requires revising certificate 

limitations and operating procedures of 

the AFM to provide the flight crew with 

runaway horizontal stabilizer trim 

procedures to follow under certain 

conditions. 


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63562 Federal Register / Vol. 83, No. 237 / Tuesday, December 11, 2018 / Rules and Regulations 

Interim Action 

We consider this AD interim action. If 

final action is later identified, we might 

consider further rulemaking then. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of 

Emergency AD 2018–23–51, issued on 

November 7, 2018, to all known U.S. 

owners and operators of these airplanes. 

The FAA found that the risk to the 

flying public justified waiving notice 

and comment prior to adoption of this 

rule because an erroneously high single 

AOA sensor input received by the flight 

control system can result in a potential 

for repeated nose-down trim commands 

of the horizontal stabilizer, which could 

cause the flight crew to have difficulty 

controlling the airplane, and lead to 

excessive nose-down attitude, 

significant altitude loss, and possible 

impact with terrain. These conditions 

still exist and the AD is hereby 

published in the Federal Register as an 

amendment to section 39.13 of the 

Federal Aviation Regulations (14 CFR 

39.13) to make it effective to all persons. 

Therefore, we find good cause that 

notice and opportunity for prior public 

comment are impracticable. In addition, 

for the reason(s) stated above, we find 

that good cause exists for making this 

amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this final rule. Send your comments to 

an address listed under the ADDRESSES

section. Include the docket number 

FAA–2018–0960 and Product Identifier 

2018–NM–151–AD at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this final rule. We will 

consider all comments received by the 

closing date and may amend this final 

rule because of those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this final rule. 

Costs of Compliance 

We estimate that this AD affects 45 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Revising the AFM ........................................... 1 work-hour × $85 per hour = $85 ................. $0 $85 $3,825 

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 

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): 

2018–23–51 The Boeing Company: 

Amendment 39–19512; Docket No. 

FAA–2018–0960; Product Identifier 

2018–NM–151–AD. 

(a) Effective Date 

This AD is effective December 21, 2018 to 

all persons except those persons to whom it 

was made immediately effective by 

Emergency AD 2018–23–51, issued on 

November 7, 2018, which contained the 

requirements of this amendment. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 737–8 and –9 airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 


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Federal Register / Vol. 83, No. 237 / Tuesday, December 11, 2018 / Rules and Regulations 63563 

(e) Unsafe Condition 

This AD was prompted by analysis 

performed by the manufacturer showing that 

if an erroneously high single angle of attack 

(AOA) sensor input is received by the flight 

control system, there is a potential for 

repeated nose-down trim commands of the 

horizontal stabilizer. We are issuing this AD 

to address this potential resulting nose-down 

trim, which could cause the flight crew to 

have difficulty controlling the airplane, and 

lead to excessive nose-down attitude, 

significant altitude loss, and possible impact 

with terrain. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revision of Airplane Flight Manual 

(AFM): Certificate Limitations 

Within 3 days after the effective date of 

this AD, revise the Certificate Limitations 

chapter of the applicable AFM to include the 

information in figure 1 to paragraph (g) of 

this AD. 

BILLING CODE 1301–00–D 

(h) AFM Revision: Operating Procedures 

Within 3 days after the effective date of 

this AD, revise the Operating Procedures 

chapter of the applicable AFM to include the 

information in figure 2 to paragraph (h) of 

this AD. 


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63564 Federal Register / Vol. 83, No. 237 / Tuesday, December 11, 2018 / Rules and Regulations 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 the attention of 

the person identified in paragraph (j) of this 

AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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 

For more information about this AD, 

contact Douglas Tsuji, Senior Aerospace 

Engineer, Systems and Equipment Section, 

FAA, Seattle ACO Branch, 2200 South 216th 

St., Des Moines, WA 98198; phone and fax: 

206–231–3548; email: Douglas.Tsuji@faa.gov. 

(k) Material Incorporated by Reference 

None. 


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Federal Register / Vol. 83, No. 237 / Tuesday, December 11, 2018 / Rules and Regulations 63565 

Issued in Des Moines, Washington, on 

November 21, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. R1–2018–26365 Filed 12–7–18; 2:00 pm] 

BILLING CODE 1301–00–C 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0796; Product 

Identifier 2018–NM–104–AD; Amendment 

39–19518; AD 2018–25–07] 

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–700–1A10 

and BD–700–1A11 airplanes. This AD 

was prompted by reports of drainage 

holes on the belly fairing forward and 

middle access panels being obstructed 

with sealant. This AD requires 

inspecting for and removing all sealant 

blocking the drainage holes on the belly 

fairing forward and middle access 

panels. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective January 15, 

2019. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 15, 2019. 

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– 

0796. 

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– 

0796; 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 

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: 

Darren Gassetto, Aerospace Engineer, 

Mechanical Systems and Administrative 

Services Section, FAA, New York ACO 

Branch, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; telephone 

516–228–7323; 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–700–1A10 and BD–700–1A11 

airplanes. The NPRM published in the 

Federal Register on September 18, 2018 

(83 FR 47113). The NPRM was 

prompted by reports of drainage holes 

on the belly fairing forward and middle 

access panels being obstructed with 

sealant. The NPRM proposed to require 

inspecting for and removing all sealant 

blocking the drainage holes on the belly 

fairing forward and middle access 

panels. 

We are issuing this AD to address 

fluid leakage that could lead to the 

accumulation of flammable fluids/ 

vapors, beyond the design capacity of 

the belly fairing venting provisions, 

which could ignite if an ignition source 

(i.e., spark, static discharge, heat, etc.) is 

present. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2018–14, 

dated May 1, 2018 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc., Model BD– 

700–1A10 and BD–700–1A11 airplanes. 

The MCAI states: 

Bombardier Aerospace (BA) has informed 

Transport Canada that the drainage holes on 

the belly fairing forward and middle access 

panels may be obstructed with sealant. The 

purpose of the drainage holes is to allow for 

drainage of a limited quantity of fluids due 

to any leaks, should they occur. This 

condition, if not corrected, may prevent the 

timely detection of fluid leakage that could 

lead to the accumulation of flammable fluids/ 

vapors, beyond the design capacity of the 

belly fairing venting provisions [which could 

ignite if an ignition source (i.e., spark, static 

discharge, heat, etc.) is present]. 

This [Canadian] AD is issued to mandate 

the removal of all sealant blocking the 

drainage holes on the belly fairing forward 

and middle access panels. 

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– 

0796. 

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 the following 

service information for Bombardier 

Model BD–700–1A10 airplanes. 

• Service Bulletin 700–53–051, dated 

May 17, 2017. 

• Service Bulletin 700–53–6009, 

dated May 17, 2017. 

Bombardier has issued the following 

service information for Bombardier 

Model BD–700–1A11 airplanes. 

• Service Bulletin 700–1A11–53–026, 

dated May 17, 2017. 

• Service Bulletin 700–53–5010, 

dated May 17, 2017. 

This service information describes 

procedures for inspecting for and 

removing sealant blocking the drainage 

holes on the belly fairing forward and 

middle access panels. These documents 

are distinct since they apply to different 

airplane models and 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 376 

airplanes of U.S. registry. We estimate 


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