46380 Federal Register / Vol. 83, No. 178 / Thursday, September 13, 2018 / Rules and Regulations 

the single stitched de-icing boots installed on 

the left-hand (LH) and right-hand (RH) 

horizontal stabilizers with double stitched 

de-icing boots and re-identify the LH and RH 

horizontal stabilizer leading edge, in 

accordance with the Accomplishment 

Instructions of Saab Service Bulletin 340–30– 

095, dated April 3, 2017. 

(j) Terminating Action for the Requirements 

of Paragraph (h) of this AD 

Modification of an airplane as required by 

paragraph (i) of this AD, constitutes 

terminating action for the repetitive 

inspections required by paragraph (h) of this 

AD, for that airplane. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards Branch, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the International Section, send it 

to the attention of the person identified in 

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

be emailed to: 9-ANM-116-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: As of the 

effective date of this AD, 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 Saab AB, 

Saab Aeronautics’ EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0144, dated August 9, 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–2018–0271. 

(2) For more information about this AD, 

contact Shahram Daneshmandi, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 2200 South 216th 

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

206–231–3220. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on October 18, 2018. 

(i) Saab Service Bulletin 340–30–095, 

dated April 3, 2017. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on August 1, 2016 (81 FR 

41432, June 27, 2016). 

(i) Saab Service Bulletin 340–30–094, 

dated March 27, 2015. 

(ii) Saab AFM 340A 001, Revision 57, 

dated March 27, 2015. 

(iii) Saab AFM 340B 001, Revision 35, 

dated March 27, 2015. 

(iv) Saab AFM 340B 010, Revision 28, 

dated March 27, 2015. 

(5) For service information identified in 

this AD, contact Saab AB, Saab Aeronautics, 

SE–581 88, Linko ̈ping, Sweden; phone: +46 

13 18 5591; fax: +46 13 18 4874; email: 

saab340techsupport@saabgroup.com; 

internet: http://www.saabgroup.com. 

(6) 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. 

(7) 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 23, 2018. 

James Cashdollar, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–19748 Filed 9–12–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0112; Product 

Identifier 2017–NM–161–AD; Amendment 

39–19392; AD 2018–18–13] 

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 all The 

Boeing Company Model 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. This AD was prompted by 

reports of cracking in certain flanges, 

and the adjacent web, of the wing 

outboard flap track at certain positions, 

and a determination that new 

inspections of certain flap track flanges 

and webs forward of the rear spar 

attachment are necessary. This AD 

requires an inspection to determine the 

part number of the wing outboard flap 

track assembly; repetitive inspections of 

each affected wing outboard flap track 

for discrepancies, and applicable oncondition actions; and repetitive 

overhaul of each wing outboard flap 

track. We are issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective October 18, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 18, 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 referenced service 

information at the FAA, Transport 

Standards Branch, 2200 South 216th St., 

Des Moines, WA. For information on the 

availability of this material at the FAA, 

call 206–231–3195. It is also available 

on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0112. 

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– 

0112; 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: 

Payman Soltani, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles 

ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5313; fax: 562–627– 

5210; email: payman.soltani@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 all The Boeing Company Model 


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737–100, –200, –200C, –300, –400, and 

–500 series airplanes. The NPRM 

published in the Federal Register on 

February 21, 2018 (83 FR 7425). The 

NPRM was prompted by reports of 

cracking in certain flanges, and the 

adjacent web, of the wing outboard flap 

track at certain positions, and a 

determination that new inspections of 

certain flap track flanges and webs 

forward of the rear spar attachment are 

necessary. The NPRM proposed to 

require an inspection to determine the 

part number of the wing outboard flap 

track assembly; repetitive inspections of 

each affected wing outboard flap track 

for discrepancies, and applicable oncondition actions; and repetitive 

overhaul of each wing outboard flap 

track. 

We are issuing this AD to detect and 

correct cracking of the wing outboard 

flap tracks. Cracking in the area between 

the forward and rear spar attachments of 

the wing outboard flap tracks could lead 

to the inability of a principal structural 

element to sustain required flight loads, 

and result in loss of the outboard 

trailing edge flap and consequent 

reduced controllability of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this final rule. 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Extend the Compliance 

Time 

All Nippon Airways (ANA) and Utair 

Aviation requested that paragraph (h) of 

the proposed AD be revised to extend 

the compliance time from 6 months to 

18 months after the effective date of the 

final rule. The commenters are 

concerned that there are not enough 

spare flap track parts available. The 

commenters indicated that overhaul of 

the removed flap tracks takes significant 

time, and if the final rule is released 

without a sufficient number of spare 

flap tracks available, there could be a 

long-term aircraft on ground (AOG) 

situation if the proposed compliance 

times are used. 

Furthermore, Utair Aviation stated 

that a review of maintenance records on 

38 airplanes for flap tracks at positions 

1 and 8 did not find any records of 

inspections or overhaul, and it would 

not be able to replace the subject flap 

tracks within the compliance time 

specified in the proposed AD. Utair 

Aviation also noted that it took 60 days, 

including shipping, to replace the 

outboard flap tracks for similar 

requirements specified in AD 2013–09– 

02, Amendment 39–17443 (78 FR 

27010, May 9, 2013). 

We do not agree with the commenters’ 

requests. The 6-month compliance time 

for inspection and overhaul is 

applicable only to flap tracks that have 

unknown maintenance records and flap 

tracks that were last overhauled several 

years ago. Airplanes with flap tracks 

that have known maintenance records 

generally have later compliance times, 

depending on how long it has been 

since the flap tracks were overhauled. 

The NPRM was issued to address 

findings of stress corrosion cracking in 

the flap tracks. Stress corrosion cracking 

is more likely to occur in flap tracks that 

have been in operation for a longer time. 

Flap tracks with unknown maintenance 

records and flap tracks that were last 

overhauled several years ago are more 

susceptible to the unsafe condition. The 

probability of the existence of stress 

corrosion cracking on flap tracks with 

unknown maintenance history is higher 

and warrants the shorter compliance 

time. We have verified that spare flap 

tracks are available on the parts surplus 

market; however, since we do not know 

how many flap tracks have unknown 

maintenance records, it is difficult to 

estimate how many spare flap tracks 

will be necessary to meet the demand. 

If there is a critical shortage of parts, 

operators may contact the FAA and 

request an adjustment to the compliance 

time using the procedures specified in 

paragraph (l) of this AD. We might 

approve a longer compliance time if 

additional data are presented that would 

justify an extension to the compliance 

time while still maintaining an adequate 

level of safety. 

We urge operators to seek out 

maintenance records for their flap tracks 

in order to justify use of the extended 

compliance times specified in Boeing 

Alert Requirements Bulletin 737– 

57A1338 RB, dated September 25, 2017. 

We cannot justify extending the 

compliance times for flap tracks without 

maintenance records to 18 months. We 

have not changed this AD in regard to 

this issue. 

Request To Omit Inspection 1 in the 

Service Information 

Utair Aviation stated that it is 

inadvisable to require operators to do 

the inspections included in 

‘‘INSPECTION 1,’’ as defined in Boeing 

Alert Requirements Bulletin 737– 

57A1338 RB, dated September 25, 2017. 

The commenter noted that ‘‘ACTION 1’’ 

in Table 1 and Table 2 of paragraph 3, 

‘‘Compliance,’’ of Boeing Alert 

Requirements Bulletin 737–57A1338 

RB, dated September 25, 2017, states 

that operators need to do INSPECTION 

1. The commenter suggested that 

‘‘ACTION 2,’’ overhaul of each affected 

flap track, would already include all of 

the inspections included in 

INSPECTION 1. 

We infer that the commenter is 

requesting that the proposed 

requirement to do the inspections 

included in INSPECTION 1 of the 

specified service bulletin be removed 

from the proposed AD. We do not agree 

with the commenter’s request. ACTION 

1 and ACTION 2 have different 

purposes. The inspections included in 

ACTION 1 are intended to detect 

specific existing damage on the flap 

track, including cracks, nicks, corrosion, 

galling, broken pieces, and stop drills. 

The intention of ACTION 2, overhaul of 

each affected flap track, is a visual 

examination for defects. The intent of 

this visual examination during overhaul 

is to identify additional discrepancies, 

such as excessive wear or degraded 

surface finish, that might not be noted 

during INSPECTION 1. It is important to 

detect these additional discrepancies 

since they can be early indicators of 

stress corrosion cracking. Since the 

inspections to detect specific existing 

damage on the flap track are not 

included in the overhaul instructions, it 

is necessary to require both ACTION 1 

and ACTION 2 in this AD. We have not 

changed this AD in regard to this issue. 

Request for Alternative To Overhaul 

ANA requested that an alternative to 

overhaul of the flap tracks be provided 

that does not involve removing the flap 

tracks from the wing. The commenter 

suggested that an on-wing inspection 

could be used instead of the overhaul. 

The commenter is concerned that there 

is not a sufficient supply of spare flap 

track parts. 

We do not agree with the commenter’s 

request. There is no on-wing inspection 

method available that can detect the 

additional discrepancies that overhaul 

of the flap tracks is designed to address. 

The concern regarding availability of 

spare flap track parts was addressed in 

the response to an earlier comment. We 

have not changed this AD in regard to 

this issue. 

Request To Revise Parts Installation 

Limitation Paragraph 

Boeing requested that the Parts 

Installation Limitation Paragraph, 

paragraph (k) in the proposed AD, be 

revised to allow flap tracks to be 

installed and inspected at the time of 

installation. Boeing noted that 

paragraph (k) states ‘‘. . . no person 

may install a flap track unless the flap 

track is inspected prior to installation.’’ 

Boeing pointed out that there are several 


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inspections that pertain to the track-towing joint, which cannot be 

accomplished until after the flap track is 

installed. 

We agree with the commenter’s 

request for the reasons provided by the 

commenter. We have revised paragraph 

(k) of this AD to state ‘‘As of the 

effective date of this AD, no person may 

install, on any airplane, a wing outboard 

flap track having a part number listed in 

paragraph 1.B. of Boeing Alert 

Requirements Bulletin 737–57A1338 

RB, dated September 25, 2017, unless 

the inspections . . . are accomplished 

prior to or concurrently with the part’s 

installation on the airplane.’’ 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

accomplishing the installation of 

winglets using Supplemental Type 

Certificate (STC) ST01219SE does not 

affect compliance with the actions 

proposed in the NPRM. 

We concur with the commenter. We 

have redesignated paragraph (c) of the 

proposed AD as paragraph (c)(1) of this 

AD and added paragraph (c)(2) to this 

AD to state that installation of STC 

ST01219SE does not affect the ability to 

accomplish the actions required by this 

AD. Therefore, for airplanes on which 

STC ST01219SE is installed, a ‘‘change 

in product’’ alternative method of 

compliance (AMOC) approval request is 

not necessary to comply with the 

requirements of 14 CFR 39.17. 

Additional Change to This AD 

The proposed AD included Note 1 to 

paragraph (h), which stated that 

guidance for accomplishing the 

proposed actions could be found in 

Boeing Alert Service Bulletin 737– 

57A1338, dated September 25, 2017, 

which is referred to in Boeing Alert 

Requirements Bulletin 737–57A1338 

RB, dated September 25, 2017. Since the 

proposed AD was published, Boeing has 

issued Boeing Information Notice 737– 

57A1338 IN 01, dated October 16, 2017; 

Boeing Information Notice 737– 

57A1338 IN 02, dated March 16, 2018; 

and Boeing Information Notice 737– 

57A1338 IN 03, dated March 20, 2018. 

These information notices provide 

additional guidance material related to 

Boeing Alert Service Bulletin 737– 

57A1338, dated September 25, 2017, 

including clarification of compliance 

times for spares (not AD compliance 

times), inspection figures, and the 

relationship between flap track part 

numbers and airplanes groups. We have 

revised Note 1 to paragraph (h) in this 

AD to include these information notices. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this 

final rule with the changes described 

previously and minor editorial changes. 

We have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

addressing the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this final rule. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert 

Requirements Bulletin 737–57A1338 

RB, dated September 25, 2017. This 

service information describes 

procedures for repetitive inspections 

and repetitive overhaul of the wing 

outboard flap tracks, and applicable oncondition actions including repair and 

replacement of the wing outboard flap 

tracks. 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 160 

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 

Inspection (positions 1 and 8; 

Group 2 and Group 3, configuration 1).

78 work-hours × $85 per hour = 

$6,630 per cycle.

$0 $6,630 per cycle ........ $1,060,800 per cycle. 

Inspection (positions 1 and 8; 

Group 3, configuration 2).

89 work-hours × $85 per hour = 

$7,565 per cycle.

0 7,565 per cycle .......... 1,210,400 per cycle. 

Inspection (positions 2 and 7; 

Group 2 and Group 3, configuration 1).

83 work-hours × $85 per hour = 

$7,055 per cycle.

0 7,055 per cycle .......... 1,128,800 per cycle. 

Inspection (positions 2 and 7; 

Group 3, configuration 2).

86 work-hours × $85 per hour = 

$7,310 per cycle.

0 7,310 per cycle .......... 1,169,600 per cycle. 

We have received no definitive data 

that will enable us to provide cost 

estimates for the actions for Group 1 

airplanes, the repetitive overhaul, or the 

on-condition actions specified in this 

AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

This AD is issued in accordance with 

authority delegated by the Executive 

Director, Aircraft Certification Service, 

as authorized by FAA Order 8000.51C. 

In accordance with that order, issuance 

of ADs is normally a function of the 

Compliance and Airworthiness 

Division, but during this transition 

period, the Executive Director has 

delegated the authority to issue ADs 

applicable to transport category 

airplanes and associated appliances to 


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Federal Register / Vol. 83, No. 178 / Thursday, September 13, 2018 / Rules and Regulations 46383 

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): 

2018–18–13 The Boeing Company: 

Amendment 39–19392; Docket No. 

FAA–2018–0112; Product Identifier 

2017–NM–161–AD. 

(a) Effective Date 

This AD is effective October 18, 2018. 

(b) Affected ADs 

This AD affects AD 2013–09–02, 

Amendment 39–17443 (78 FR 27010, May 9, 

2013) (‘‘AD 2013–09–02’’). 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes, 

certificated in any category. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/ebd1cec7b301293e86257

cb30045557a/$FILE/ST01219SE.pdf) does 

not affect the ability to accomplish the 

actions required by this AD. Therefore, for 

airplanes on which STC ST01219SE is 

installed, a ‘‘change in product’’ alternative 

method of compliance (AMOC) approval 

request is not necessary to comply with the 

requirements of 14 CFR 39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking in certain flanges, and the adjacent 

web, of the wing outboard flap track at 

certain positions, and a determination that 

new inspections of certain flap track flanges 

and webs forward of the rear spar attachment 

are necessary. We are issuing this AD to 

detect and correct cracking of the wing 

outboard flap tracks. Cracking in the area 

between the forward and rear spar 

attachments of the wing outboard flap tracks 

could lead to the inability of a principal 

structural element to sustain required flight 

loads, and result in loss of the outboard 

trailing edge flap and consequent reduced 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions for Group 1 Airplanes 

For airplanes identified as Group 1 in 

Boeing Alert Requirements Bulletin 737– 

57A1338 RB, dated September 25, 2017: 

Within 120 days after the effective date of 

this AD, do actions to correct the unsafe 

condition using a method approved in 

accordance with the procedures specified in 

paragraph (l) of this AD. 

(h) Required Actions 

For airplanes not specified in paragraph (g) 

of this AD: Except as required by paragraph 

(i) of this AD, at the applicable times 

specified in the ‘‘Compliance’’ paragraph of 

Boeing Alert Requirements Bulletin 737– 

57A1338 RB, dated September 25, 2017, do 

all applicable actions identified in, and in 

accordance with, the Accomplishment 

Instructions of Boeing Alert Requirements 

Bulletin 737–57A1338 RB, dated September 

25, 2017. 

Note 1 to paragraph (h) of this AD: 

Guidance for accomplishing the actions 

required by this AD can be found in Boeing 

Alert Service Bulletin 737–57A1338, dated 

September 25, 2017, which is referred to in 

Boeing Alert Requirements Bulletin 737– 

57A1338 RB, dated September 25, 2017. 

Additional guidance can be found in Boeing 

Information Notice 737–57A1338 IN 01, 

dated October 16, 2017; Boeing Information 

Notice 737–57A1338 IN 02, dated March 16, 

2018; and Boeing Information Notice 737– 

57A1338 IN 03, dated March 20, 2018. 

(i) Exceptions to Service Information 

Specifications 

For purposes of determining compliance 

with the requirements of this AD: Where 

Boeing Alert Requirements Bulletin 737– 

57A1338 RB, dated September 25, 2017, uses 

the phrase ‘‘the original issue date of 

Requirements Bulletin 737–57A1338 RB,’’ 

this AD requires using ‘‘the effective date of 

this AD.’’ 

(j) Terminating Action for Requirements of 

AD 2013–09–02 

Accomplishment of the requirements 

specified in paragraph (h) of this AD 

terminates all requirements of AD 2013–09– 

02. 

(k) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install, on any airplane, a wing 

outboard flap track having a part number 

listed in paragraph 1.B. of Boeing Alert 

Requirements Bulletin 737–57A1338 RB, 

dated September 25, 2017, unless the 

inspections and corrective actions specified 

in the Accomplishment Instructions of 

Boeing Alert Requirements Bulletin 737– 

57A1338 RB, dated September 25, 2017, are 

accomplished prior to or concurrently with 

the part’s installation on the airplane. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 (m)(1) of 

this AD. Information may be emailed to: 9- 

ANM-LAACO-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, Los Angeles 

ACO Branch, 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. 

(m) Related Information 

(1) For more information about this AD, 

contact Payman Soltani, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

Lakewood, CA 90712 4137; phone: 562–627– 

5313; fax: 562–627–5210; email: 

payman.soltani@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 


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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 Alert Requirements Bulletin 

737–57A1338 RB, dated September 25, 2017. 

(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/ibr-locations.html. 

Issued in Des Moines, Washington, on 

August 24, 2018. 

James Cashdollar, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–19185 Filed 9–12–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0418; Product 

Identifier 2017–SW–016–AD; Amendment 

39–19390; AD 2018–18–11] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Model AS–365N2 and AS 

365 N3 helicopters with a lower strobe 

light installed. This AD requires 

installing a cable mount, inspecting the 

lower strobe light wiring harness, and 

re-routing the wiring harness. This AD 

was prompted by reports of interference 

between the lower strobe light wiring 

harness and the helicopter structure. 

The actions of this AD are intended to 

prevent an unsafe condition on these 

helicopters. 

DATES: This AD is effective October 18, 

2018. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of October 18, 2018. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http://

www.helicopters.airbus.com/website/ 

en/ref/Technical-Support_73.html. You 

may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy., Room 6N–321, 

Fort Worth, TX 76177. It is also 

available on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0418. 

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– 

0418; 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 

European Aviation Safety Agency 

(EASA) AD, any incorporated-byreference service information, the 

economic evaluation, any comments 

received, and other information. The 

street 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: 

George Schwab, Aviation Safety 

Engineer, Safety Management Section, 

Rotorcraft Standards Branch, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5110; email 

george.schwab@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 11, 2018, at 83 FR 21964, 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 

Airbus Helicopters Model AS–365N2 

and AS 365 N3 helicopters with a lower 

strobe light installed. 

The NPRM proposed to require 

installing a cable mount on the 

helicopter structure and inspecting the 

lower strobe light electrical harness and 

the electrical harness between the cutoff connector and Frame 2000 for torn 

spiral tape and for any chafing on the 

harness cables. If the spiral tape is torn, 

the NPRM proposed to require replacing 

the spiral tape. If there is any chafing on 

the cable, the NPRM proposed to require 

replacing the harness. The proposed 

requirements were intended to prevent 

interference between the lower strobe 

light electrical harness wiring and the 

helicopter structure, which could result 

in chafing of an electrical harness 

adjacent to the inboard fuel tank vapor 

space, a fuel tank fire, and subsequent 

loss of control of the helicopter. 

The NPRM was prompted by AD No. 

2016–0258, dated December 16, 2016, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for Airbus Helicopters Model 

AS 365 N2 and AS 365 N3 helicopters 

with certain serial numbers and 

configurations. EASA advises of inproduction helicopters with lower 

strobe light wiring harnesses that were 

interfering with either the helicopter 

structure or the adjacent fuel tank 

support. EASA further states that an 

investigation determined that the 

electrical harnesses of these lower 

strobe lights were manufactured with 

additional length to facilitate removal 

and installation of the lower strobe light 

assembly. However, the additional 

length of wiring in the harness was not 

properly secured to the helicopter 

structure. According to EASA, this 

could result in chafing of the harness on 

the helicopter structure, creating an 

ignition source adjacent to the inboard 

fuel tank vapor space, and result in a 

fuel tank fire. 

To address this unsafe condition, the 

EASA AD requires installing a cable 

mount, inspecting the lower strobe light 

electrical harness for damage, and rerouting the electrical harness. 

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 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 


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