Federal Register / Vol. 83, No. 169 / Thursday, August 30, 2018 / Rules and Regulations 44207 

the effective date of this AD: Conduct the 

inspection within 72 months after the most 

recent inspection. 

(ii) For airplanes that have not been 

inspected as specified in 28–AWL–22 as of 

the effective date of this AD: Conduct the 

inspection within 12 months after the 

effective date of this AD. 

(6) For AWL No. 28–AWL–24, ‘‘Motor 

Operated Valve Bonding Jumper 

Installation—Fault Current Protection’’: At 

the applicable time specified in paragraph 

(g)(6)(i) or (g)(6)(ii) of this AD. 

(i) For airplanes that have been previously 

inspected as specified in 28–AWL–24 as of 

the effective date of this AD: Conduct the 

inspection within 60 months after the most 

recent inspection. 

(ii) For airplanes that have not been 

inspected as specified in 28–AWL–24 as of 

the effective date of this AD: Conduct the 

inspection within 12 months after the 

effective date of this AD. 

(h) Additional Acceptable Wire Types and 

Sleeving 

As an option, when accomplishing the 

actions required by paragraph (g) of this AD, 

the changes specified in paragraphs (h)(1) 

and (h)(2) of this AD can be made to AWL 

No. 28–AWL–03. 

(1) Where AWL No. 28–AWL–03 identifies 

wire types BMS 13–48, BMS 13–58, and BMS 

13–60, add the following acceptable wire 

types: MIL–W–22759/16, SAE AS22759/16 

(M22759/16), MIL–W–22759/32, SAE 

AS22759/32 (M22759/32), MIL–W–22759/34, 

SAE AS22759/34 (M22759/34), MIL–W– 

22759/41, SAE AS22759/41 (M22759/41), 

MIL–W–22759/86, SAE AS22759/86 

(M22759/86), MIL–W–22759/87, SAE 

AS22759/87 (M22759/87), MIL–W–22759/92 

and SAE AS22759/92 (M22759/92); and 

MIL–C–27500 and NEMA WC 27500 cables 

constructed from these military or SAE 

specification wire types identified above. 

(2) Where AWL No. 28–AWL–03 identifies 

TFE–2X Standard wall for wire sleeving, add 

the following acceptable sleeving materials: 

Roundit 2000NX and Varglas Type HO, HP, 

or HM. 

(i) No Alternative Actions, Intervals, and 

Critical Design Configuration Control 

Limitations (CDCCLs) 

After the maintenance or inspection 

program, as applicable, has been revised as 

required by paragraph (g) of this AD, no 

alternative actions (e.g., inspections), 

intervals, and CDCCLs may be used unless 

the actions, intervals, and CDCCLs are 

approved as an alternative method of 

compliance (AMOC), in accordance with the 

procedures specified in paragraph (k) of this 

AD. 

(j) Terminating Actions 

Accomplishment of the maintenance or 

inspection program revision required by 

paragraph (g) of this AD terminates the 

actions specified in paragraphs (j)(1) through 

(j)(5) of this AD. 

(1) The revision required by paragraph (g) 

of AD 2008–04–10 R1. 

(2) The revision required by paragraph (h) 

of AD 2009–05–03. 

(3) The revision required by paragraph (j) 

of AD 2011–12–05. 

(4) The revision required by paragraph (h) 

of AD 2013–22–03. 

(5) The revision required by paragraphs 

(n)(1) and (n)(2) of AD 2013–24–15. 

(k) 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 (l) 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. 

(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, Seattle ACO 

Branch, FAA, 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. 

(l) Related Information 

For more information about this AD, 

contact Christopher Baker, Aerospace 

Engineer, Propulsion Section, FAA, Seattle 

ACO Branch, 2200 South 216th St., Des 

Moines, WA 98198; phone and fax: 206–231– 

3552; email: christopher.r.baker@faa.gov. 

(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 the AD specifies otherwise. 

(i) Boeing 727–100/200 Airworthiness 

Limitations (AWLs) D6–8766–AWL, Revision 

December 2016. 

(ii) Reserved. 

(3) For 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 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 17, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–18664 Filed 8–29–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0036; Product 

Identifier 2017–SW–015–AD; Amendment 

39–19354; AD 2018–16–14] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Inc., Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Bell 

Helicopter Textron Inc. (Bell) Model 

212, Model 412, and Model 412EP 

helicopters. This AD requires replacing 

the emergency flotation system (EFS) 

tube assembly. This AD was prompted 

by a report of an EFS tube assembly 

failure. The actions of this AD are 

intended to address an unsafe condition 

on these products. 

DATES: This AD is effective October 4, 

2018. 

ADDRESSES: For service information 

identified in this final rule, contact Bell 

Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, TX 76101; telephone (817) 

280–3391; fax (817) 280–6466; or at 

http://www.bellcustomer.com/files/. 

You may review a copy of the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy., Room 6N–321, Fort Worth, TX 

76177. 

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– 

0036; 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 AD, the 

economic evaluation, any comments 

received, and other information. The 

street address for Docket Operations 

(phone: 800–647–5527) is U.S. 


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44208 Federal Register / Vol. 83, No. 169 / Thursday, August 30, 2018 / Rules and Regulations 

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: Rory 

Rieger, Aviation Safety Engineer, DSCO 

Branch, AIR–7J0, FAA, 10101 Hillwood 

Pkwy., Fort Worth, TX 76177; telephone 

(817) 222–5193; email rory.rieger@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On January 26, 2018, at 83 FR 3630, 

the Federal Register published our 

notice of proposed rulemaking (NPRM), 

which proposed to amend 14 CFR part 

39 by adding an AD that would apply 

to Bell Model 212, Model 412, and 

Model 412EP helicopters with a certain 

EFS tube assembly installed. The NPRM 

proposed to require, within 300 hours 

time-in-service (TIS), replacing any EFS 

tube assembly part number (P/N) 412– 

073–820–101 with an unknown 

manufacture date or that was 

manufactured before July 28, 2016. The 

NPRM also proposed to prohibit 

installing on any helicopter an EFS tube 

assembly P/N 412–073–820–101 that 

was manufactured before July 28, 2016 

or that has an unknown manufacture 

date. 

The NPRM was prompted by a report 

from Bell that an EFS tube assembly 

separated from the valve during a 2-year 

inflation test. A subsequent 

investigation found that excessive 

sleeve preset force during 

manufacturing caused cracks in the 

sleeve of the tube assembly, which may 

result in the EFS float failing to deploy. 

Bell determined that only those EFS 

tube assemblies with P/N 412–073–820– 

101 that were shipped prior to July 28, 

2016, were subject to this manufacturing 

defect. Bell states that because this 

manufacturing defect is difficult to 

detect, affected EFS tube assemblies in 

service must be replaced. The affected 

parts were associated with a single Bell 

supplier that is no longer manufacturing 

the tube assembly. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM. 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

Related Service Information 

We reviewed Bell Alert Service 

Bulletin (ASB) 212–11–143 for Bell 

Model 212 helicopters, and ASB 412– 

11–147 for Bell Model 412 and 412EP 

helicopters, both Revision C and dated 

December 22, 2016. Each ASB describes 

and illustrates procedures to replace the 

tube assembly within 600 flight hours or 

by March 31, 2017. 

Differences Between This AD and the 

Service Information 

The service information requires 

compliance within 600 flight hours or 

by March 31, 2017; this AD requires 

compliance within 300 hours TIS. 

Costs of Compliance 

We estimate that this AD will affect 

250 helicopters of U.S. Registry. 

We estimate that operators will incur 

the following costs in order to comply 

with this AD. At an average labor rate 

of $85 per hour, replacing a tube 

assembly will require about 6 workhours and required parts will cost 

$4,902, for a total cost of $5,412 per 

helicopter and $1,353,000 for the U.S. 

fleet. 

According to Bell’s service 

information, some of the costs of this 

AD may be covered under warranty, 

thereby reducing the cost impact on 

affected individuals. We do not control 

warranty coverage by Bell. Accordingly, 

we have included all costs in our cost 

estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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): 

2018–16–14 Bell Helicopter Textron Inc.: 

Amendment 39–19354; Docket No. 

FAA–2018–0036; Product Identifier 

2017–SW–015–AD. 

(a) Applicability 

This AD applies to Bell Helicopter Textron 

Inc. Model 212, Model 412, and Model 412EP 

helicopters, certificated in any category, with 

an emergency flotation system (EFS) tube 

assembly part number (P/N) 412–073–820– 

101 with a date of manufacture before July 

28, 2016, or an unknown date of manufacture 

installed. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack on an EFS tube assembly. This 

condition could result in failure of the 


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Federal Register / Vol. 83, No. 169 / Thursday, August 30, 2018 / Rules and Regulations 44209 

emergency floats to inflate during an 

emergency water landing. 

(c) Effective Date 

This AD becomes effective October 4, 2018. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) Within 300 hours time-in-service: 

(i) Remove the EFS tube assembly from 

service. 

(ii) Lubricate the shoulder of the sleeves, 

threads, and seat of each mating fitting with 

anti-seize compound. 

(iii) Install an EFS tube assembly not listed 

in paragraph (a) of this AD. 

(2) After the effective date of this AD, do 

not install an EFS tube assembly listed in 

paragraph (a) of this AD on any helicopter. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, DSCO Branch, FAA, may 

approve AMOCs for this AD. Send your 

proposal to: Rory Rieger, Aviation Safety 

Engineer, DSCO Branch, AIR–7J0, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5193; email 

rory.rieger@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

Bell Helicopter Alert Service Bulletins 

212–11–143 and 412–11–147, both Revision 

C and dated December 22, 2016, which are 

not incorporated by reference, contain 

additional information about the subject of 

this AD. For service information identified in 

this AD, contact Bell Helicopter Textron, 

Inc., P.O. Box 482, Fort Worth, TX 76101; 

telephone (817) 280–3391; fax (817) 280– 

6466; or at http://www.bellcustomer.com/ 

files/. You may review a copy of information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 3212 Emergency Flotation Section. 

Issued in Fort Worth, Texas, on August 3, 

2018. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2018–18735 Filed 8–29–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0300; Product 

Identifier 2017–NM–134–AD; Amendment 

39–19375; AD 2018–17–21] 

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 certain 

Airbus SAS Model A318, A319, and 

A320 series airplanes; and Model A321– 

111, –112, –131, –211, –212, –213, –231, 

–232, –251N, –253N, and –271N 

airplanes. This AD was prompted by a 

revision of an airworthiness limitations 

document that specifies more restrictive 

maintenance requirements and 

airworthiness limitations. This AD 

requires revising the maintenance or 

inspection program, as applicable, to 

incorporate revised fuel airworthiness 

limitations. We are issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective October 4, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 4, 2018. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus SAS, Airworthiness Office— 

EIAS, 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–2018– 

0300. 

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– 

0300; 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3223. 

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 Airbus SAS Model 

A318, A319, and A320 series airplanes; 

and Model A321–111, –112, –131, –211, 

–212, –213, –231, –232, –251N, –253N, 

and –271N airplanes. The NPRM 

published in the Federal Register on 

April 27, 2018 (83 FR 18485). The 

NPRM was prompted by a revision of an 

airworthiness limitations document that 

specifies more restrictive maintenance 

requirements and airworthiness 

limitations. The NPRM proposed to 

require revising the maintenance or 

inspection program, as applicable, to 

incorporate revised fuel airworthiness 

limitations. 

We are issuing this AD to address the 

potential of ignition sources inside fuel 

tanks, which, in combination with 

flammable fuel vapors, could result in a 

fuel tank explosion and consequent loss 

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 2017–0169, 

dated September 7, 2017 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus SAS Model A318, A319, 

and A320 series airplanes; and Model 

A321–111, –112, –131, –211, –212, 

–213, –231, –232, –251N, –253N, and 

–271N airplanes. The MCAI states: 

The Fuel Airworthiness Limitations (FAL) 

for Airbus A320 family aeroplanes, which are 

approved by EASA, are currently defined and 

published in the Airbus A318/A319/A320/ 

A321 Airworthiness Limitations Section 

(ALS) Part 5 document. These instructions 

have been identified as mandatory for 

continued airworthiness. Failure to 

accomplish these instructions could result in 

a fuel tank explosion and consequent loss of 

the aeroplane. 


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