Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Proposed Rules 40505 

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 

removing airworthiness directive (AD) 

2013–11–09, Amendment 39–17469 (78 

FR 32551, May 31, 2013), and adding 

the following new AD: 

Safran Helicopter Engines, S.A. (Type 

Certificate previously held by 

Turbomeca S.A): Docket No. FAA–2013– 

0024; Product Identifier 2000–NE–12– 

AD. 

(a) Comments Due Date 

We must receive comments by October 10, 

2017. 

(b) Affected ADs 

This AD supersedes AD 2013–11–09, 

Amendment 39–17469 (78 FR 32551, May 31, 

2013). 

(c) Applicability 

This AD applies to all Turbomeca S.A. 

Arrius 2B1 and 2F turboshaft engines. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7320, Fuel Controlling System. 

(e) Unsafe Condition 

This AD was prompted by several reports 

of engine flameouts as a result of reduced 

fuel flow due to the presence of coking. We 

are issuing this AD to prevent an engine 

flameout of Arrius 2B1 and 2F turboshaft 

engines and damage to the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For Arrius 2B1 turboshaft engines, do 

the following: 

(i) Replace each main fuel injector halfmanifold and preferred injector with a part 

eligible for installation before exceeding the 

operating hours (hours accumulated by the 

part since installation on an engine) specified 

in Figure 1 to paragraph (g) of this AD. 

FIGURE 1 TO PARAGRAPH (g)— 

REPLACEMENT

Part Operating 

hours 

Main fuel injector half-manifold—post-mod TU117 ...... 600 

Main fuel injector half-manifold—pre-mod TU117 ....... 200 

Preferred injector pre/postmod TU117 ....................... 200 

(ii) Borescope-inspect (BSI) the flame tube 

and the high-pressure turbine (HPT) area for 

turbine distress, when replacing the fuel 

injector manifolds and preferred injector for 

the first time. 

(iii) Thereafter, replace the fuel injector 

manifolds and preferred injector with a part 

eligible for installation before exceeding the 

operating hours (hours accumulated by the 

part since installation on an engine) specified 

in Figure 1 to paragraph (g) of this AD. 

(2) For Arrius 2F turboshaft engines, do the 

following: 

(i) Replace each pipe injector preferred 

assembly, part number (P/N) 0 319 73 835 0 

and P/N 0 319 73 044 0, with a part eligible 

for installation before exceeding 400 

operating hours (hours accumulated by the 

part since installation on an engine). 

(ii) BSI the flame tube and the HPT area 

for turbine distress, when replacing the 

privilege injector for the first time. 

(iii) Unless already accomplished as 

required by paragraph (g)(2)(i) of this AD, 

within 16 months after the effective date of 

this AD, replace the pipe injector preferred 

assembly, P/N 0 319 73 835 0, with a part 

eligible for installation before the next flight. 

(iv) Thereafter, replace the pipe injector 

preferred assembly with a part eligible for 

installation within 400 operating hours since 

the last pipe injector preferred assembly 

replacement. 

(h) Definitions 

(1) For Arrius 2B1 turboshaft engines, a 

main fuel injector half-manifold or preferred 

injector is eligible for installation if it has not 

exceeded the operating hours specified in 

Figure 1 to paragraph (g) of this AD since first 

installation on an engine or since last 

cleaning. 

(2) For Arrius 2F turboshaft engines, a pipe 

injector preferred assembly, P/N 0 319 73 044 

0, is eligible for installation if it has not 

exceeded 400 operating hours since first 

installation on an engine or since last 

cleaning. 

(i) Installation Prohibition 

(1) For Arrius 2B1 turboshaft engines, after 

the effective date of this AD, do not install 

a main fuel injector half-manifold or 

preferred injector onto any engine, or any 

engine onto a helicopter, unless the main fuel 

injector half-manifold and preferred injector 

are eligible for installation. 

(2) For Arrius 2F turboshaft engines, after 

the effective date of this AD, do not install 

a pipe injector preferred assembly onto any 

engine, or any engine onto a helicopter, 

unless the pipe injector preferred assembly is 

eligible for installation. 

(3) For Arrius 2F turboshaft engines, after 

the effective date of this AD, do not install 

a pipe injector preferred assembly, P/N 0 319 

73 835 0, onto any engine. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, FAA, ECO Branch, 

Compliance and Airworthiness Division, 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 ECO Branch, send it to 

the attention of the person identified in 

paragraph (k)(1) 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. 

(k) Related Information 

(1) For more information about this AD, 

contact Robert Green, Aerospace Engineer, 

FAA, ECO Branch, Compliance and 

Airworthiness Division, 1200 District 

Avenue, Burlington, MA 01803; phone: 781– 

238–7754; fax: 781–238–7199; email: 

robert.green@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency (EASA) AD 2017–0070, dated 

April 25, 2017, for more information. You 

may examine the MCAI in the AD docket on 

the Internet at http://www.regulations.gov by 

searching for and locating it in Docket No. 

FAA–2013–0024. 

(3) Safran Helicopter Engines S.A., SB No. 

319 73 4839, Version A, dated December 13, 

2016, can be obtained from Safran Helicopter 

Engines S.A., using the contact information 

in paragraph (k)(4) of this AD. 

(4) For service information identified in 

this AD, contact Safran Helicopter Engines, 

S.A., 40220 Tarnos, France; phone: (33) 05 59 

74 40 00; fax: (33) 05 59 74 45 15. 

(5) You may view this service information 

at the FAA, Engine and Propeller Standards 

Branch, Policy and Innovation Division, 1200 

District Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

August 18, 2017. 

Robert J. Ganley, 

Manager, Engine and Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2017–17829 Filed 8–24–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0805; Product 

Identifier 2017–NM–051–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all The 

Boeing Company Model DC–9–81 (MD– 

81), DC–9–82 (MD–82), DC–9–83 (MD– 

83), DC–9–87 (MD–87) airplanes, Model 

MD–88 airplanes, and Model MD–90–30 

airplanes. This proposed AD was 

prompted by a report of loss of airspeed 


pmangrum on DSK3GDR082PROD with PROPOSALS
40506 Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Proposed Rules 

indication due to icing. This proposed 

AD would require modifying the air 

data heat (ADH) system. We are 

proposing this AD to address the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed AD by October 10, 2017. 

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. 

For service information identified in 

this NPRM, 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, 

1601 Lind Avenue SW., Renton, WA. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2017–0805. 

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–2017– 

0805; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Eric 

Igama, Aerospace Engineer, Systems 

and Equipment Section, FAA, Los 

Angeles ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5388; fax: 562–627– 

5210; email: roderick.igama@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2017–0805; Product Identifier 2017– 

NM–051–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD 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 proposed AD. 

Discussion 

We have received a report of both 

pilots’ airspeed indicators freezing at 80 

knots during takeoff. The outside air 

temperature was 25 degrees Fahrenheit 

and the wind was at approximately 20 

knots in light snow. The airplane had 

been waiting in this weather condition 

for about two hours for de-icing before 

takeoff. 

Air data sensors directly affect flight 

computers and flight deck 

instrumentation. The air data sensors 

have heaters to prevent blockage from 

ice formation in the sensor or from ice 

formation on the static plates. Incorrect 

airspeed indications can be the direct 

result of pitot tube icing. Failure to 

activate the ADH system in icing 

conditions could result in irregular 

airspeed or altitude indications, which 

could possibly result in a runway 

overrun during a high speed rejected 

takeoff (RTO) due to failure to rotate 

before the end of the runway, or a stall/ 

overspeed during flight. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin MD80–30A132, dated April 28, 

2017; and Boeing Alert Service Bulletin 

MD90–30A031, dated June 2, 2017. This 

service information describes 

procedures for modifying the ADH 

system so that it activates when the left 

and right fuel switches are in the ON 

position. These documents are distinct 

since they apply to different airplane 

models. 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. 

FAA’s Determination 

We are proposing 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 these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require 

accomplishment of the actions 

identified as ‘‘RC’’ (required for 

compliance) in the Accomplishment 

Instructions of the service information 

described previously, except for 

differences between this proposed AD 

and the service information that are 

identified in the regulatory text of this 

proposed AD. For information on the 

procedures, see this service information 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2017–0805. 

Master Minimum Equipment List 

relief may be developed and approved 

by the FAA Long Beach, CA Aircraft 

Evaluation Group (AEG) Flight 

Operations Evaluation Board (FOEB) to 

allow operation of an airplane with an 

ADH system modified in accordance 

with this proposed AD that is 

inoperable for a specified time period. 

This potential relief is specified in 

paragraph (i) of this proposed AD. 

Differences Between This Proposed AD 

and the Service Information 

Boeing Alert Service Bulletin MD80– 

30A132, dated April 28, 2017, specifies 

to contact the manufacturer for change 

instructions, but this proposed AD 

would require obtaining and doing 

those change instructions in one of the 

following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

affects 553 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 


pmangrum on DSK3GDR082PROD with PROPOSALS
Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Proposed Rules 40507 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Modification, MD80 Group 1, 84 airplanes ..... 56 work-hours × $85 per hour = $4,760 ........ $4,459 $9,219 $774,396 

Modification, MD80 Group 2, 11 airplanes ..... 57 work-hours × $85 per hour = $4,845 ........ 11,014 15,859 174,449 

Modification, MD80 Group 3, 336 airplanes ... 57 work-hours × $85 per hour = $4,845 ........ 8,589 13,434 4,513,824 

Modification, MD80 Group 4, 1 airplane ......... 56 work-hours × $85 per hour = $4,760 ........ 4,479 9,239 9,239 

Modification, MD80 Group 5, 37 airplanes ..... 57 work-hours × $85 per hour = $4,845 ........ 11,034 15,879 587,523 

Modification, MD90 Group 1, 84 airplanes ..... 37 work-hours × $85 per hour = $3,145 ........ 4,395 7,540 633,360 

We have received no definitive data 

that would enable us to provide cost 

estimates for doing the modification on 

MD80 Group 6 airplanes. 

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 proposed 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 to the Director of the 

System Oversight Division. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

The Boeing Company: Docket No. FAA– 

2017–0805; Product Identifier 2017– 

NM–051–AD. 

(a) Comments Due Date 

We must receive comments by October 10, 

2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model DC–9–81 (MD–81), DC–9– 

82 (MD–82), DC–9–83 (MD–83), DC–9–87 

(MD–87) airplanes, Model MD–88 airplanes, 

and Model MD–90–30 airplanes, certificated 

in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 3410; Flight environment data. 

(e) Unsafe Condition 

This AD was prompted by a report of loss 

of airspeed indication due to icing. We are 

issuing this AD to prevent operation of 

unheated air data sensors in icing conditions. 

Failure to activate the air data heat (ADH) 

system in icing conditions could result in 

irregular airspeed or altitude indications, 

which could possibly result in a runway 

overrun during a high speed rejected takeoff 

(RTO) due to failure to rotate before the end 

of the runway, or a stall/overspeed during 

flight. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

At the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD: Do all 

applicable actions identified as ‘‘RC’’ 

(required for compliance) in, and in 

accordance with, the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD80–30A132, dated April 28, 2017; and 

Boeing Alert Service Bulletin MD90–30A031, 

dated June 2, 2017; as applicable; except as 

required by paragraph (h) of this AD. 

(1) For Model DC–9–81 (MD–81), DC–9–82 

(MD–82), DC–9–83 (MD–83), DC–9–87 (MD– 

87) model airplanes and Model MD–88 

airplanes: Within 28 months after the 

effective date of this AD. 

(2) For Model MD–90–30 airplanes: Within 

27 months after the effective date of this AD. 

(h) Exception to Service Information 

Specifications 

Where Boeing Alert Service Bulletin 

MD80–30A132, dated April 28, 2017, 

specifies contacting Boeing, and specifies 

that action as ‘‘RC’’ (Required for 

Compliance): This AD requires using a 

method approved in accordance with the 

procedures specified in paragraph (j) of this 

AD. 

(i) Master Minimum Equipment List (MMEL) 

In the event that the ADH system as 

modified by this AD is inoperable, an 

airplane may be operated as specified in the 

FAA-approved MMEL, provided MMEL 

provisions that address the modified ADH 

system are included in the MMEL and those 

provisions are included in the operator’s 

Minimum Equipment List. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles ACO Branch, 

FAA, has the authority to approve AMOCs 


pmangrum on DSK3GDR082PROD with PROPOSALS
40508 Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Proposed Rules 

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 (k)(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. 

(4) Except as required by paragraph (h) of 

this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (j)(4)(i) and (j)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. An AMOC is required for any 

deviations to RC steps, including substeps 

and identified figures. 

(ii) Steps not labeled 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 RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(k) Related Information 

(1) For more information about this AD, 

contact Eric Igama, Aerospace Engineer, 

Systems and Equipment Section, FAA, Los 

Angeles ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5388; fax: 562–627–5210; 

email: roderick.igama@faa.gov. 

(2) 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. You may view this 

referenced service information at the FAA, 

Transport Standards Branch, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on August 

16, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–17839 Filed 8–24–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0778; Product 

Identifier 2017–NM–038–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 757–200 

series airplanes. This proposed AD was 

prompted by an evaluation by the 

design approval holder (DAH) 

indicating that the side panel-to-frame 

attachments and frames of the aft cargo 

compartment are subject to widespread 

fatigue damage (WFD). This proposed 

AD would require an inspection of the 

side panel-to-frame attachments and 

frames to verify that certain 

modifications have been done, and 

applicable on-condition actions. We are 

proposing this AD to address the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed AD by October 10, 2017. 

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. 

For service information identified in 

this NPRM, 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, 

1601 Lind Avenue SW., Renton, WA. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2017–0778. 

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–2017– 

0778; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Muoi Vuong, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles 

ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5205; fax: 562–627– 

5210; email: Muoi.Vuong@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2017–0778; Product Identifier 2017– 

NM–038–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD 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 proposed AD. 

Discussion 

Fatigue damage can occur locally, in 

small areas or structural design details, 

or globally, in widespread areas. 

Multiple-site damage is widespread 

damage that occurs in a large structural 

element such as a single rivet line of a 


pmangrum on DSK3GDR082PROD with PROPOSALS