Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules 27721 

Accomplishment Instructions of Boeing 

Service Bulletin MD11–28–137, dated June 

24, 2014. 

(ii) Prior to or concurrently with 

accomplishing the actions specified in 

paragraph (h)(1)(i) of this AD: Replace the 

fuel pump control relays with fault current 

detectors, and change the fuel tank boost/ 

transfer pump wire termination, in 

accordance with Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD11–28A133, dated June 5, 2014. 

(2) For Model DC–10–10, DC–10–10F, DC– 

10–15, DC–10–30, DC–10–30F (KC–10A and 

KDC–10), DC–10–40, DC–10–40F, MD–10– 

10F, and MD–10–30F airplanes: Do the 

actions specified in paragraphs (h)(2)(i) and 

(h)(2)(ii) of this AD. 

(i) As of 48 months after April 15, 2016 

(the effective date of AD 2016–04–16), 

change the fuel pump control and indication 

system wiring, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin DC10–28–256, dated June 

24, 2014. 

(ii) Prior to or concurrently with 

accomplishing the actions specified in 

paragraph (h)(2)(i) of this AD: Replace the 

fuel pump control relays with fault current 

detectors, and change the fuel tank boost/ 

transfer pump wire termination, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

DC10–28A253, dated June 5, 2014. 

(3) For all airplanes: Within 30 days after 

accomplishing the actions required by 

paragraph (h)(1) or (h)(2) of this AD, or 

within 30 days after April 15, 2016 (the 

effective date of AD 2016–04–16), whichever 

occurs later, revise the maintenance or 

inspection program, as applicable, to 

incorporate the Critical Design Configuration 

Control Limitations (CDCCLs), Airworthiness 

Limitation Instructions (ALIs), and shortterm extensions specified in Appendices B, 

C, and D of Boeing Trijet Special Compliance 

Item (SCI) Report MDC–02K1003, Revision 

M, dated July 25, 2014. The initial 

compliance time for accomplishing the 

actions specified in the ALIs is at the later 

of the times specified in paragraphs (h)(3)(i) 

and (h)(3)(ii) of this AD. Revising the 

maintenance or inspection program required 

by this paragraph terminates the 

requirements in paragraphs (g) and (h) of AD 

2008–06–21 R1. 

(i) At the applicable time specified in 

Appendix C of Boeing Trijet SCI Report 

MDC–02K1003, Revision M, dated July 25, 

2014, except as provided by Appendix D of 

Boeing Trijet SCI Report MDC–02K1003, 

Revision M, dated July 25, 2014. 

(ii) Within 30 days after accomplishing the 

actions required by paragraph (h)(1) or (h)(2) 

of this AD, as applicable; or within 30 days 

after April 15, 2016 (the effective date of AD 

2016–04–16); whichever occurs later. 

(i) Restatement of Paragraph (i) of AD 2016– 

04–16, With No Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2016–04–16, with no 

changes. If the option in paragraph (h)(3) of 

this AD is accomplished: After the 

maintenance or inspection program has been 

revised as provided by paragraph (h)(3) of 

this AD, no alternative actions (e.g., 

inspections), intervals, or CDCCLs may be 

used unless the actions, intervals, or CDCCLs 

are approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (l) of this 

AD. 

(j) Restatement of Paragraph (j) of AD 2016– 

04–16, With Additional AD Reference and 

Clarification of Provisions 

This paragraph restates the provisions of 

paragraph (j) of AD 2016–04–16, with an 

additional AD reference and clarification of 

the provisions. Accomplishment of the 

actions specified in paragraphs (h)(1), (h)(2), 

and (h)(3) of this AD, as applicable, extends 

the 18-month interval for the repetitive 

inspections and tests required by paragraph 

(a) of AD 2002–13–10; the 18-month interval 

for the repetitive inspections required by 

paragraph (a) of AD 2003–07–14; and the 18- 

month interval for the repetitive inspections 

required by paragraph (j) of AD 2011–11–05; 

to 24-month intervals for pumps affected by 

those ADs, regardless if the pump is installed 

in a tank that normally empties, provided the 

remaining actions required by those three 

ADs have been accomplished. 

(k) New Provision of This AD: Optional 

Terminating Action 

Replacing the electrical connectors or fuel 

pump housing in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin DC10–28–264, dated May 

15, 2015; or Boeing Service Bulletin MD11– 

28–146, dated May 15, 2015, as applicable; 

terminates the repetitive inspections and 

tests required by paragraph (a) of AD 2002– 

13–10, paragraph (a) of AD 2003–07–14, and 

paragraph (j) of AD 2011–11–05. 

(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. 

(4) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (l)(4)(i) and (l)(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. 

(m) Related Information 

(1) For more information about this AD, 

contact Serj Harutunian, Aerospace Engineer, 

Propulsion Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

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

5254; fax: 562–627–5210; email: 

serj.harutunian@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, 2200 South 

216th St., Des Moines, WA. For information 

on the availability of this material at the 

FAA, call 206–231–3195. 

Issued in Des Moines, Washington, on June 

6, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–12656 Filed 6–13–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0511; Product 

Identifier 2017–NM–145–AD] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited 

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 BAE 

Systems (Operations) Limited Model 

4101 airplanes. This proposed AD was 

prompted by a determination that 


daltland on DSKBBV9HB2PROD with PROPOSALS
27722 Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules 

inspection requirements for a number of 

maintenance tasks are incorrect. This 

proposed AD would require a one-time 

detailed inspection of a certain fuselage 

frame and repair, if necessary, and a 

revision of the maintenance or 

inspection program, as applicable, to 

incorporate new or revised maintenance 

instructions and airworthiness 

limitations. We are proposing this AD to 

address the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by July 30, 2018. 

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 BAE Systems 

(Operations) Limited, Customer 

Information Department, Prestwick 

International Airport, Ayrshire, KA9 

2RW, Scotland, United Kingdom; 

telephone +44 1292 675207; fax +44 

1292 675704; email RApublications@

baesystems.com; internet http://

www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 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. 

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– 

0511; 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 NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3228. 

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– 

2018–0511; Product Identifier 2017– 

NM–145–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this NPRM. We will consider 

all comments received by the closing 

date and may amend this NPRM based 

on 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 NPRM. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2017–0187, 

dated September 22, 2017 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all BAE Systems (Operations) 

Limited Model 4101 airplanes. The 

MCAI states: 

Maintenance instructions for BAE 

Jetstream 4100 aeroplanes, which are 

approved by EASA, are defined in BAE 

Systems (Operations) Ltd Jetstream 4100 

Service Bulletin (SB) J41–51–001, which 

references certain Aircraft Maintenance 

Manual (AMM) tasks. These instructions 

have been identified as mandatory for 

continued airworthiness. 

Failure to accomplish these instructions 

could result in an unsafe condition. 

CAA UK [Civil Aviation Authority United 

Kingdom] issued AD 005–02–2002 [which 

corresponds to FAA AD 2005–15–11, 

Amendment 39–14200 (70 FR 43025, July 26, 

2005) (‘‘AD 2005–15–11’’)] to require 

operators to comply with the inspection 

instructions as referenced in SB J41–51–001 

at original issue. 

Since that [CAA UK] AD was issued, BAE 

Systems (Operations) Ltd have determined 

that the inspection requirements for a 

number of maintenance tasks are incorrect. 

Consequently, existing inspection items 52– 

20–013, 53–10–006, 53–10–025, 53–10–029 

and 53–10–079 will be amended in Chapter 

05 of the AMM. Compliance periods for these 

changes are given in BAE Systems 

(Operations) Ltd SB J41–51–001 (now at 

Revision 4) and BAE Systems (Operations) 

Ltd Alert SB J41–A53–058. Those fatigue 

inspections detailed in SB J41–51–001, at 

Revision 3 or earlier, have now been 

incorporated into Chapter 05 of the AMM. To 

avoid duplication these tasks are deleted 

from SB J41–51–001 at Revision 4. 

For the reason described above, this 

[EASA] AD retains the requirements of CAA 

UK AD 005–02–2002, which is superseded, 

and requires accomplishment of the actions 

specified in BAE Systems (Operations) Ltd 

Jetstream 4100 SB J41–51–001 Revision 4 and 

Alert SB J41–A53–058 (hereafter collectively 

referred to as ‘the SB’ in this [EASA] AD). 

The actions include a one-time 

detailed inspection of fuselage frame 90 

for cracking or fatigue damage and 

repair if necessary; and revising the 

maintenance or inspection program, as 

applicable, to incorporate new or 

revised maintenance instructions and 

airworthiness limitations. This 

proposed AD was prompted by a 

determination that it is possible for 

cracks in fuselage frame 90 to exceed 

the critical length for failure in less time 

than the current inspection interval; and 

a determination that inspection 

requirements for a number of 

maintenance tasks involving certain 

airworthiness limitations are incorrect. 

The unsafe condition is cracking in 

fuselage frame 90, which could cause it 

to fail and thereby compromise the 

structural integrity of the aircraft 

pressure hull; and fatigue damage of 

various airplane structures, which could 

result in reduced structural integrity of 

the airplane. 

You may examine the MCAI in the 

AD docket on the internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0511. 

Relationship Between Proposed AD and 

AD 2005–15–11 

This NPRM would not supersede AD 

2005–15–11. Rather, we have 

determined that a stand-alone AD 

would be more appropriate to address 

the changes in the MCAI. This NPRM 

would require a one-time detailed 

inspection of fuselage frame 90 for 

cracking or fatigue damage and revising 

the maintenance or inspection program, 

as applicable, to incorporate new or 

revised maintenance instructions and 

airworthiness limitations. 

Accomplishment of the proposed 

actions would then terminate all of the 

requirements of AD 2005–15–11. 

Related Service Information Under 1 

CFR Part 51 

BAE Systems (Operations) Limited 

has issued the following service 

information. 

• Service Bulletin J41–51–001, 

Revision 4, dated July 11, 2017. This 

service information describes new 


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inspections and revisions to existing 

inspection requirements and thresholds. 

• Alert Service Bulletin J41–A53–058, 

dated December 6, 2016. This service 

information describes procedures for a 

detailed inspection for cracking or 

fatigue damage of fuselage frame 90. 

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 and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

This AD requires revisions to certain 

operator maintenance documents to 

include new actions (e.g., inspections). 

Compliance with these actions is 

required by 14 CFR 91.403(c). For 

airplanes that have been previously 

modified, altered, or repaired in the 

areas addressed by this proposed AD, 

the operator may not be able to 

accomplish the actions described in the 

revisions. In this situation, to comply 

with 14 CFR 91.403(c), the operator 

must request approval for an alternative 

method of compliance according to 

paragraph (l)(1) of this proposed AD. 

The request should include a 

description of changes to the required 

actions that will ensure the continued 

damage tolerance of the affected 

structure. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

The MCAI specifies that if there are 

findings from the airworthiness 

limitations section (ALS) inspection 

tasks, corrective actions must be 

accomplished in accordance with 

Airbus maintenance documentation. 

However, this proposed AD does not 

include that requirement. Operators of 

U.S.-registered airplanes are required by 

general airworthiness and operational 

regulations to perform maintenance 

using methods that are acceptable to the 

FAA. We consider those methods to be 

adequate to address any corrective 

actions necessitated by the findings of 

ALS inspections required by this 

proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 4 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection ................................ 2 work-hours × $85 per hour = $170 ..................................... $0 $170 $680 

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). 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed 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 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. 


daltland on DSKBBV9HB2PROD with PROPOSALS
27724 Federal Register / Vol. 83, No. 115 / Thursday, June 14, 2018 / Proposed Rules 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

BAE Systems (Operations) Limited: Docket 

No. FAA–2018–0511; Product Identifier 

2017–NM–145–AD. 

(a) Comments Due Date 

We must receive comments by July 30, 

2018. 

(b) Affected ADs 

This AD affects AD 2005–15–11, 

Amendment 39–14200 (70 FR 43025, July 26, 

2005) (‘‘AD 2005–15–11’’). 

(c) Applicability 

This AD applies to all BAE Systems 

(Operations) Limited Model 4101 airplanes, 

certificated in any category, all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Time Limits/Maintenance 

Checks. 

(e) Reason 

This AD was prompted by a determination 

that it is possible for cracks in fuselage frame 

90 to exceed the critical length for failure in 

less time than the current inspection interval; 

and a determination that inspection 

requirements for a number of maintenance 

tasks involving certain airworthiness 

limitations are incorrect. We are issuing this 

AD to address cracking in fuselage frame 90, 

which could cause it to fail and thereby 

compromise the structural integrity of the 

aircraft pressure hull. We are also issuing this 

AD to address fatigue damage of various 

airplane structures, which could result in 

reduced structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

At the compliance times specified in 

paragraphs (g)(1) and (g)(2) of this AD, as 

applicable: Do a detailed inspection of 

fuselage frame 90 for cracking or fatigue 

damage, in accordance with the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Alert Service 

Bulletin J41–A53–058, dated December 6, 

2016. If any cracking or fatigue damage is 

found: Before further flight, repair using a 

method approved by the Manager, 

International Section, Transport Standards 

Branch, FAA; or the European Aviation 

Safety Agency (EASA); or BAE Systems 

(Operations) Limited’s EASA Design 

Organization Approval (DOA). 

(1) For airplanes with 6,300 flight cycles or 

fewer since Structural Significant Items (SSI) 

53–10–029 (Maintenance Planning Document 

(MPD) 531029–DVl–10010–1) was last 

accomplished: Within 6,600 flight cycles 

after the last accomplishment of SSI 53–10– 

029 (MPD 531029–DVl–10010–1), or within 6 

months after the effective date of this AD, 

whichever is later. 

(2) For airplanes with more than 6,300 

flight cycles since SSI 53–10–029 (MPD 

531029–DVl–10010–1) was last 

accomplished: Within 300 flight cycles or 4.5 

months, whichever is earlier, since the last 

accomplishment of SSI 53–10–029 (MPD 

531029–DVl–10010–1), or within 6 months 

after the effective date of this AD, whichever 

is later. 

(h) Maintenance or Inspection Program 

Revisions 

Within 90 days after the effective date of 

this AD: Revise the maintenance or 

inspection program, as applicable, by 

incorporating the maintenance tasks and 

associated thresholds and intervals described 

in, and in accordance with, the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Service 

Bulletin J41–51–001, Revision 4, dated July 

11, 2017, as applicable. The initial 

compliance times for new or revised tasks are 

at the applicable times specified in BAE 

Systems (Operations) Limited Service 

Bulletin J41–51–001, Revision 4, dated July 

11, 2017, or within 6 months after the 

effective date of this AD, whichever is later. 

(i) No Alternative Actions and Intervals 

After the maintenance or inspection 

program has been revised as required by 

paragraph (h) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (l)(1) of 

this AD. 

(j) Terminating Action for Requirements of 

AD 2005–15–11 

Accomplishment of the actions required by 

paragraph (h) of this AD terminates all 

requirements of AD 2005–15–11. 

(k) No Reporting Requirement 

Although the Accomplishment Instructions 

of BAE Systems (Operations) Limited Alert 

Service Bulletin J41–A53–058, dated 

December 6, 2016, specify to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

(l) 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 (m)(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 

BAE Systems (Operations) Limited’s EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0187, dated September 22, 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–2018–0511. 

(2) For more information about this AD, 

contact Todd Thompson, Aerospace 

Engineer, International Section, Transport 

Standards Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax 206–231–3228. 

(3) For service information identified in 

this AD, contact BAE Systems (Operations) 

Limited, Customer Information Department, 

Prestwick International Airport, Ayrshire, 

KA9 2RW, Scotland, United Kingdom; 

telephone +44 1292 675207; fax +44 1292 

675704; email RApublications@

baesystems.com; internet http://

www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 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. 

Issued in Des Moines, Washington, on June 

6, 2018. 

Michael Kaszycki, 

Acting Director, System Oversight Division, 

Aircraft Certification Service. 

[FR Doc. 2018–12732 Filed 6–13–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0512; Product 

Identifier 2017–NM–170–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

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 

Airbus Model A318, A319, A320 and 

A321 series airplanes. This AD requires 

revising the maintenance or inspection 


daltland on DSKBBV9HB2PROD with PROPOSALS