44204 Federal Register / Vol. 83, No. 169 / Thursday, August 30, 2018 / Rules and Regulations 

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): 

2018–17–22 Airbus SAS: Amendment 39– 

19376; Docket No. FAA–2018–0411; 

Product Identifier 2017–NM–157–AD. 

(a) Effective Date 

This AD is effective October 4, 2018. 

(b) Affected ADs 

This AD affects AD 2016–25–23, 

Amendment 39–18749 (81 FR 90971, 

December 16, 2016) (‘‘AD 2016–25–23’’). 

(c) Applicability 

This AD applies to Airbus SAS Model 

A319–115 and –132 airplanes, and Model 

A320–214, –216, –232, and –233 airplanes, 

certificated in any category, all manufacturer 

serial numbers on which Airbus modification 

154327 has been embodied in production, 

except those on which Airbus modification 

158740 has been embodied. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by a report 

indicating that certain modified airplanes do 

not have electrical ground wires on the fuel 

level sensing control unit (FLSCU), which 

adversely affects the fuel gravity feeding 

operation. We are issuing this AD to prevent 

reduced fuel pressure at the engine inlet, 

potentially resulting in an uncommanded inflight shutdown when flying at the fuel 

gravity feed ceiling levels. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

Within 24 months after the effective date 

of this AD, modify the FLSCU wiring in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

28–1242, Revision 01, dated October 3, 2017. 

(h) Terminating Action for AD 2016–25–23 

and Amendment of the Airplane Flight 

Manual (AFM) 

Modification of an airplane as required by 

paragraph (g) of this AD terminates all of the 

requirements of AD 2016–25–23 for that 

airplane. After modification of an airplane as 

required by paragraph (g) of this AD, remove 

Airbus A318/A319/A320/A321 Temporary 

Revision TR695, Issue 1.0, dated August 1, 

2016; or Airbus A318/A319/A320/A321 

Temporary Revision TR699, Issue 1.0, dated 

August 1, 2016; as applicable; and Airbus 

A318/A319/A320/A321 Temporary Revision 

TR700, Issue 1.0, dated August 1, 2016, from 

the applicable AFM of that airplane. 

(i) 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 

A320–28–1242, dated December 21, 2016. 

(j) 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 (k)(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 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 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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0216, dated October 30, 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–2018–0411. 

(2) For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport Standards 

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

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

3223. 

(l) 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 A320–28–1242, 

Revision 01, dated October 3, 2017. 

(ii) Reserved. 

(3) For Airbus SAS service information 

identified in this AD, contact Airbus SAS, 

Airworthiness Office—EIAS, Rond-Point 

Emile Dewoitine No: 2, 31700 Blagnac Cedex, 

France; phone: +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 17, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–18662 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–2018–0031; Product 

Identifier 2017–NM–127–AD; Amendment 

39–19374; AD 2018–17–20] 

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 727 

airplanes. This AD was prompted by 

significant changes made to the 

airworthiness limitations (AWLs) 

related to fuel tank ignition prevention. 

This AD requires revising the 

maintenance or inspection program, as 

applicable, to incorporate the latest 

revision of the AWLs. We are issuing 

this AD to address the unsafe condition 

on these products. 


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Federal Register / Vol. 83, No. 169 / Thursday, August 30, 2018 / Rules and Regulations 44205 

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 

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. 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– 

0031. 

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– 

0031; 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: 

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. 

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 The Boeing Company 

Model 727 airplanes. The NPRM 

published in the Federal Register on 

February 8, 2018 (83 FR 5576). The 

NPRM was prompted by significant 

changes made to the AWLs related to 

fuel tank ignition prevention. The 

NPRM proposed to require revising the 

maintenance or inspection program, as 

applicable, to incorporate the latest 

revision of the AWLs. 

We are issuing this AD to address the 

potential for ignition sources inside fuel 

tanks caused by latent failures, 

alterations, repairs, or maintenance 

actions, which, in combination with 

flammable fuel vapors, could result in 

fuel tank explosions and consequent 

loss of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

We have considered the comment 

received. Boeing supported the NPRM. 

Clarification of Affected Airplanes in 

Paragraph (g)(4)(ii) of This AD 

The phrase ‘‘as of the effective date of 

this AD’’ was inadvertently not 

included in the description of affected 

airplanes in paragraph (g)(4)(ii) of the 

proposed AD. We have revised 

paragraph (g)(4)(ii) of this AD 

accordingly. 

Clarification of Alternative Wire Types 

and Sleeving 

Paragraph (h) of this AD allows 

operators to revise AWL No. 28–AWL– 

03 to identify certain alternative wire 

types and sleeving materials. AWL No. 

28–AWL–03 was originally mandated 

by AD 2008–04–10 R1, Amendment 39– 

16121 (74 FR 66227, December 15, 

2009) (‘‘AD 2008–04–10 R1’’). Since the 

issuance of AD 2008–04–10 R1, which 

will be terminated by this AD, we 

received numerous requests for 

approval of alternative methods of 

compliance (AMOCs) from operators 

and supplemental type certificate (STC) 

holders (or applicants) to allow the 

installation of the alternative wire types 

and sleeving identified in paragraphs 

(h)(1) and (h)(2) of this AD. We 

evaluated certain attributes of those 

alternative wire types and sleeving for 

each installation, and issued numerous 

AMOC approvals based on our 

determination that the installation of 

those wire types and sleeving would 

provide an acceptable level of safety. 

Although paragraph (h) of this AD 

provides certain allowances, it does not 

provide approval of alternative wire 

types and sleeving that are installed as 

part of an aircraft design change. Each 

applicant for any design change is still 

responsible to show that the installation 

of alternative wire types and sleeving 

identified in paragraphs (h)(l) and (h)(2) 

of this AD complies with all applicable 

regulatory requirements. This 

responsibility includes, but is not 

limited to, substantiation of compliance 

with flammability requirements, and 

substantiation to show that sleeve 

installation, including the selection of 

sleeve thickness, is adequate to protect 

wires from chafing for the life of 

installation. If such an installation is 

found to be compliant with all 

applicable regulatory requirements, 

revision of AWL No. 28–AWL–03 in 

accordance with paragraph (h) of this 

AD would allow the installation of the 

alternative wire types and sleeving. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this 

final rule with the change 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 Boeing 727–100/200 

Airworthiness Limitations (AWLs) D6– 

8766–AWL, Revision December 2016. 

This service information describes AWL 

tasks that include airworthiness 

limitation instructions (ALIs) and 

critical design configuration control 

limitations (CDCCLs) related to fuel tank 

ignition prevention. 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 20 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

We have determined that revising the 

maintenance or inspection program 

takes an average of 90 work-hours per 

operator, although we recognize that 

this number may vary from operator to 

operator. In the past, we have estimated 

that this action takes 1 work-hour per 

airplane. Since operators incorporate 

maintenance or inspection program 

changes for their affected fleet(s), we 

have determined that a per-operator 

estimate is more accurate than a perairplane estimate. Therefore, we 

estimate the total cost per operator to be 

$7,650 (90 work-hours × $85 per workhour). 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 


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44206 Federal Register / Vol. 83, No. 169 / Thursday, August 30, 2018 / Rules and Regulations 

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): 

2018–17–20 The Boeing Company: 

Amendment 39–19374; Docket No. 

FAA–2018–0031; Product Identifier 

2017–NM–127–AD. 

(a) Effective Date 

This AD is effective October 4, 2018. 

(b) Affected ADs 

This AD affects the ADs specified in 

paragraphs (b)(1) through (b)(5) of this AD. 

(1) AD 2008–04–10 R1, Amendment 39– 

16121 (74 FR 66227, December 15, 2009) 

(‘‘AD 2008–04–10 R1’’). 

(2) AD 2009–05–03, Amendment 39–15827 

(74 FR 8851, February 27, 2009) (‘‘AD 2009– 

05–03’’). 

(3) AD 2011–12–05, Amendment 39–16712 

(76 FR 33991, June 10, 2011) (‘‘AD 2011–12– 

05’’). 

(4) AD 2013–22–03, Amendment 39–17635 

(78 FR 65193, October 31, 2013) (‘‘AD 2013– 

22–03’’). 

(5) AD 2013–24–15, Amendment 39–17692 

(78 FR 72791, December 4, 2013) (‘‘AD 2013– 

24–15’’). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 727, 727C, 727–100, 727–100C, 727– 

200, and 727–200F series airplanes, 

certificated in any category, with an original 

certificate of airworthiness or original export 

certificate of airworthiness issued on or 

before the effective date of this AD. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by significant 

changes made to the airworthiness 

limitations (AWLs) related to fuel tank 

ignition prevention. We are issuing this AD 

to prevent the potential for ignition sources 

inside fuel tanks caused by latent failures, 

alterations, repairs, or maintenance actions, 

which, in combination with flammable fuel 

vapors, could result in fuel tank explosions 

and consequent loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Maintenance or Inspection Program 

Revision 

Within 60 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate all 

information in Section A, including 

Subsections A.1 and A.2, of Boeing 727–100/ 

200 Airworthiness Limitations (AWLs) D6– 

8766–AWL, Revision December 2016. The 

initial compliance times for the airworthiness 

limitation instruction (ALI) items are within 

the applicable compliance times specified in 

paragraphs (g)(1) through (g)(6) of this AD. 

(1) For AWL No. 28–AWL–01, ‘‘External 

Wires Over Center Fuel Tank (Tank No. 2)’’: 

At the applicable time specified in paragraph 

(g)(1)(i) or (g)(1)(ii) of this AD. 

(i) For airplanes that have been previously 

inspected as specified in 28–AWL–01 as of 

the effective date of this AD: Conduct the 

inspection within 120 months after the most 

recent inspection. 

(ii) For airplanes that have not been 

inspected as specified in 28–AWL–01 as of 

the effective date of this AD: Conduct the 

inspection within 12 months after the 

effective date of this AD. 

(2) For AWL No. 28–AWL–16, ‘‘OverCurrent and Arcing Protection Electrical 

Design Features Operation—Boost Pump 

Ground Fault Interrupter (GFI)’’: At the 

applicable time specified in paragraph 

(g)(2)(i) or (g)(2)(ii) of this AD. 

(i) For airplanes that have been previously 

inspected as specified in 28–AWL–16 as of 

the effective date of this AD: Conduct the 

inspection within 12 months after the most 

recent inspection. 

(ii) For airplanes that have not been 

inspected as specified in 28–AWL–16 as of 

the effective date of this AD: Conduct the 

inspection within 90 days after the effective 

date of this AD. 

(3) For AWL No. 28–AWL–17, ‘‘Auxiliary 

Tank Fuel Boost Pump Power Failed On 

Protection System’’: At the applicable time 

specified in paragraph (g)(3)(i) or (g)(3)(ii) of 

this AD. 

(i) For airplanes that have been previously 

inspected as specified in 28–AWL–17 as of 

the effective date of this AD: Conduct the 

inspection within 12 months after the most 

recent inspection. 

(ii) For airplanes that have not been 

inspected as specified in 28–AWL–17 as of 

the effective date of this AD: Conduct the 

inspection within 90 days after the effective 

date of this AD. 

(4) For AWL No. 28–AWL–18, ‘‘Fuel 

Quantity Indicating System (FQIS)—OutTank Wiring Lightning Shield to Ground 

Termination and Joint Resistance for the 

Volumetric Top-Off (VTO) Unit (If 

Installed)’’: At the applicable time specified 

in paragraph (g)(4)(i) or (g)(4)(ii) of this AD. 

(i) For airplanes that have been previously 

inspected as specified in 28–AWL–18 as of 

the effective date of this AD: Conduct the 

inspection within 120 months after the most 

recent inspection. 

(ii) For airplanes that have not been 

inspected as specified in 28–AWL–18 as of 

the effective date of this AD: Conduct the 

inspection within 12 months after the 

effective date of this AD. 

(5) For AWL No. 28–AWL–22, ‘‘AC Fuel 

Boost Pump Bonding Installation’’: At the 

applicable time specified in paragraph 

(g)(5)(i) or (g)(5)(ii) of this AD. 

(i) For airplanes that have been previously 

inspected as specified in 28–AWL–22 as of 


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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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