Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 3053 

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): 

Fokker Services B.V.: Docket No. FAA– 

2015–8467; Directorate Identifier 2014– 

NM–107–AD. 

(a) Comments Due Date 

We must receive comments by March 7, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model F.28 Mark 1000, 2000, 3000, and 4000 

airplanes, certificated in any category, all 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by a design review 

that revealed no controlled bonding 

provisions are present on a number of critical 

locations inside the fuel tanks or connected 

to the walls of the fuel tanks. We are issuing 

this AD to prevent an ignition source in the 

fuel tank vapor space, which could result in 

a fuel tank explosion and consequent loss of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Installation of Bonding Provisions 

At the next scheduled opening of the fuel 

tanks after the effective date of this AD, but 

no later than 84 months after the effective 

date of this AD, install additional and 

improved bonding provisions in the fuel 

tanks, and do the applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Fokker Services Proforma 

Service Bulletin SBF28–28–058, dated 

January 9, 2014, including Appendix SBF28– 

28–058/APP01, dated July 15, 2014. 

(h) Revision of Maintenance or Inspection 

Program 

Before further flight after completing the 

installation specified in paragraph (g) of this 

AD, or within 30 days after the effective date 

of this AD, whichever occurs later: Revise the 

airplane maintenance or inspection program, 

as applicable, by incorporating the fuel 

airworthiness limitation items and critical 

design configuration control limitations 

(CDCCLs) specified in paragraph 1.L.(1)(c) of 

Fokker Services Proforma Service Bulletin 

SBF28–28–058, dated January 9, 2014, 

including Appendix SBF28–28–058/APP01, 

dated July 15, 2014. The initial compliance 

times for the tasks are at the latest of the 

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

and (h)(3) of this AD. 

(1) At the applicable time specified in 

Fokker Service Bulletin SBF28–28–050, 

Revision 3, dated December 11, 2014. 

(2) Before further flight after completing 

the installation specified in paragraph (g) of 

this AD. 

(3) Within 30 days after the effective date 

of this AD. 

(i) No Alternative Actions, Intervals, and 

CDCCLs 

After accomplishment of the revision 

required by paragraph (h) 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 (j)(1) of this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance: 

The Manager, International Branch, ANM– 

116, Transport Airplane Directorate, 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 Branch, send it 

to ATTN: Tom Rodriguez, Aerospace 

Engineer, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 1601 

Lind Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@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. The AMOC approval letter 

must specifically reference this AD. 

(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 Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Fokker B.V. Service’s EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2014–0108, dated May 8, 2014, 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–2015–8467. 

(2) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 1357, 

2130 EL Hoofddorp, the Netherlands; 

telephone +31 (0)88–6280–350; fax +31 

(0)88–6280–111; email technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.com. You may view this 

service information at the FAA, Transport 

Airplane Directorate, 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 January 

5, 2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00636 Filed 1–19–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0922; Directorate 

Identifier 2014–NM–156–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain Airbus Model A319 and 

A320 series airplanes. The NPRM 

proposed to require the modification of 

eight fastener locations in the longeron 

area below the emergency exit cut-outs 

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

(RH) sides. The NPRM was prompted by 

a report that fatigue cracking could 

appear at certain fastener locations in 

the longeron area below the emergency 

exit cut-outs. This proposed AD is 

intended to complete certain mandated 

programs intended to support the 

airplane reaching its limit of validity 

(LOV) of the engineering data that 

support the established structural 

maintenance program. This action 


tkelley on DSK3SPTVN1PROD with PROPOSALS
3054 Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 

revises the applicability by adding postAirbus modification 32208 airplanes, 

which are also affected. We are 

proposing this supplemental NPRM 

(SNPRM) to detect and correct cracking 

at certain fastener locations in the 

longeron area below the emergency exit 

cut-outs, which could lead to failure of 

the fasteners and reduced structural 

integrity of the airplane. Since these 

actions impose an additional burden 

over those proposed in the NPRM, we 

are reopening the comment period to 

allow the public the chance to comment 

on these proposed changes. 

DATES: We must receive comments on 

this SNPRM by March 7, 2016. 

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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. You may view this 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

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–2014– 

0922; 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 

(telephone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0922; Directorate Identifier 

2014–NM–156–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 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 proposed AD. 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Airbus Model A319 and 

A320 series airplanes. The NPRM 

published in the Federal Register on 

December 15, 2014 (79 FR 74035). 

The NPRM was prompted by a report 

that fatigue cracking could appear at 

certain fastener locations in the 

longeron area below the emergency exit 

cut-outs. The NPRM was intended to 

complete certain mandated programs 

intended to support the airplane 

reaching its LOV of the engineering data 

that support the established structural 

maintenance program. The NPRM 

proposed to require the modification of 

eight fastener locations in the longeron 

area below the emergency exit cut-outs 

on the LH and RH sides. 

Actions Since Previous NPRM (79 FR 

74035, December 15, 2014) Was Issued 

Since we issued the NPRM (79 FR 

74035, December 15, 2014), we have 

determined that airplanes having Airbus 

modification 32208, which were 

excluded from the applicability of 

NPRM (79 FR 74035, December 15, 

2014), are also affected. For this reason, 

the FAA added airplanes having Airbus 

modification 32208 to the applicability 

of this proposed AD and increased the 

number of airplanes in the Costs of 

Compliance section to 294 airplanes. 

The European Aviation Safety Agency, 

which is the Technical Agent for the 

Member States of the European Union, 

has issued EASA Airworthiness 

Directive 2015–0085, dated May 13, 

2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition on certain Model 

A319 and Model A320 series airplanes. 

The MCAI states: 

During the A320 fatigue test campaign for 

Extended Service Goal (ESG), it was 

determined that fatigue damage could appear 

at certain fastener locations on the longeron 

[area] below the emergency exit cut-outs, on 

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

of the fuselage. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To address this potential unsafe condition, 

Airbus developed a modification, which has 

been published through Airbus Service 

Bulletin (SB) A320–53–1265 for in-service 

application to allow aeroplanes to operate up 

to the new ESG limit. Consequently, EASA 

issued AD 2014–0176 to require modification 

(cold working) of 8 fastener locations in the 

longeron area (Stringer 20A) below the 

emergency exit cut-outs on the LH and RH 

sides. 

Since that [EASA] AD was issued, it was 

identified that post-mod 32208 aeroplanes, 

which were excluded from the Applicability 

of that [EASA] AD, are also affected. 

For the reason described above, this 

[EASA] AD retains the requirements of EASA 

AD 2014–0176, which is superseded, but no 

longer excludes post-mod 32208 aeroplanes 

from the Applicability. 

As described in FAA Advisory 

Circular 120–104 (http://www.faa.gov/

documentLibrary/media/Advisory_

Circular/120-104.pdf), several programs 

have been developed to support 

initiatives that will ensure the 

continued airworthiness of aging 

airplane structure. The last element of 

those initiatives is the requirement to 

establish a LOV of the engineering data 

that support the structural maintenance 

program under 14 CFR 26.21. This 

proposed AD is the result of an 

assessment of the previously established 

programs by the design approval holder 

(DAH) during the process of establishing 

the LOV for Airbus Model A319 and 

A320 series airplanes. The actions 

specified in this proposed AD are 

necessary to complete certain programs 

to ensure the continued airworthiness of 

aging airplane structure and to support 

an airplane reaching its LOV. 

You may examine the MCAI in the 

AD docket on the Internet at http://


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 3055 

www.regulations.gov/

#!documentDetail;D=FAA-2014-0922. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–53–1265, Revision 02, dated July 

10, 2014. The service information 

describes procedures for modifying the 

fastener locations in the longeron area 

below the emergency exit cut-outs on 

both RH and LH sides of the fuselage. 

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. 

Comments 

We gave the public the opportunity to 

participate in developing this proposed 

AD. We considered the comment 

received. The following presents the 

comment received on the NPRM (79 FR 

74035, December 15, 2014) and the 

FAA’s response to the comment. 

Request To Allow the Use of Later 

Revisions of Service Bulletin 

United Airlines (United) requested 

that the NPRM (79 FR 74035, December 

15, 2014) contain a statement allowing 

use of later revisions of the service 

information as an acceptable method of 

compliance for the proposed AD. United 

stated the modification addressed by the 

NPRM allows operators to reach an ESG. 

United stated that the service 

information mentioned in the NPRM 

may not incorporate the proper 

effectivity, since Airbus Service Bulletin 

A320–53–1265, Revision 01, dated July 

2, 2013, is restricted to operators who 

have applied for Airbus’s request for 

change/request for modification order 

(RFC/RMO) process. United stated the 

effectivity of Airbus Service Bulletin 

A320–53–1265, Revision 02, dated July 

10, 2014, will likely not agree with the 

applicability of the NPRM. 

We partially agree. We disagree to 

allow use of later revisions of service 

documents in an AD because use of 

unpublished service information is not 

allowed by the Office of the Federal 

Register’s regulations for approving 

materials incorporated by reference. 

However, we have reviewed Airbus 

Service Bulletin A320–53–1265, 

Revision 02, dated July 10, 2014, which 

updated the kit information and the 

effectivity. We revised the applicability 

in this proposed AD to reflect the 

effectivity of Airbus Service Bulletin 

A320–53–1265, Revision 02, dated July 

10, 2014. We also revised the references 

in paragraph (g) of this proposed AD to 

refer to Airbus Service Bulletin A320– 

53–1265, Revision 02, dated July 10, 

2014, and revised paragraph (h) of this 

proposed AD to allow credit for actions 

done using Airbus Service Bulletin 

A320–53–1265, Revision 01, dated July 

2, 2013. Affected operators may request 

approval to use a later revision of the 

referenced service information as an 

Alternative Method of Compliance 

(AMOC) using the procedures specified 

in paragraph (i) of this proposed AD. 

FAA’s Determination and Requirements 

of This SNPRM 

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 these same 

type designs. 

Certain changes described above 

expand the scope of the NPRM (79 FR 

74035, December 15, 2014). As a result, 

we have determined that it is necessary 

to reopen the comment period to 

provide additional opportunity for the 

public to comment on this SNPRM. 

Explanation of ‘‘RC’’ Procedures and 

Tests in Service Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which procedures and tests 

in the service information are required 

for compliance with an AD. 

Differentiating these procedures and 

tests from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The procedures and tests 

identified as RC (required for 

compliance) in any service information 

have a direct effect on detecting, 

preventing, resolving, or eliminating an 

identified unsafe condition. 

As specified in a NOTE under the 

Accomplishment Instructions of the 

specified service information, 

procedures and tests that are identified 

as RC in any service information must 

be done to comply with the proposed 

AD. However, procedures and tests that 

are not identified as RC are 

recommended. Those procedures and 

tests that are not identified as RC may 

be deviated from using accepted 

methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of 

an alternative method of compliance 

(AMOC), provided the procedures and 

tests identified as RC can be done and 

the airplane can be put back in an 

airworthy condition. Any substitutions 

or changes to procedures or tests 

identified as RC will require approval of 

an AMOC. 

Costs of Compliance 

We estimate that this SNPRM affects 

294 airplanes of U.S. registry. 

We estimate that it would take about 

12 work-hours per product to comply 

with the new basic requirements of this 

SNPRM. The average labor rate is $85 

per work-hour. Required parts would 

cost about $0 per product. Based on 

these figures, we estimate the cost of 

this SNPRM on U.S. operators to be 

$299,880, or $1,020 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

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); 


tkelley on DSK3SPTVN1PROD with PROPOSALS
3056 Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 

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): 

Airbus: Docket No. FAA–2014–0922; 

Directorate Identifier 2014–NM–156–AD. 

(a) Comments Due Date 

We must receive comments by March 7, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1) and (c)(2) of 

this AD, certificated in any category, except 

those on which Airbus modification (mod) 

152637 has been embodied in production. 

(1) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes, 

all manufacturer serial numbers (MSN). 

(2) Airbus Model A320–211, –212, –214, 

–231, –232, and –233 airplanes, all 

manufacturer serial numbers (MSN). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report that 

fatigue cracking could appear at certain 

fastener locations in the longeron area below 

the emergency exit cut-outs. We are issuing 

this AD to detect and correct cracking at 

certain fastener locations in the longeron area 

below the emergency exit cut-outs, which 

could lead to failure of the fasteners and 

reduced structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification of Fastener Locations 

Before the accumulation of 48,000 total 

flight cycles or 96,000 total flight hours, 

whichever occurs first since the airplane’s 

first flight, modify the 8 fastener locations in 

the longeron area (stringer 20A) below the 

emergency exit cut-outs on both RH and LH 

sides, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1265, Revision 02, 

dated July 10, 2014. 

(h) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–53–1265, dated January 2, 

2013; or Airbus Service Bulletin A320–53– 

1265, Revision 01, dated July 2, 2013; which 

are not incorporated by reference in this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@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. The AMOC approval letter 

must specifically reference this AD. 

(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 Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0085, dated 

May 13, 2015, for related information. This 

MCAI may be found in the AD docket on the 

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

#!documentDetail;D=FAA-2014-0922-0002. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

You may view this referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. You may view this service information 

at the FAA, Transport Airplane Directorate, 

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 January 

5, 2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00699 Filed 1–19–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8469; Directorate 

Identifier 2014–NM–105–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. 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 

Fokker Services B.V. Model F.28 Mark 

1000, 2000, 3000, and 4000 airplanes. 

This proposed AD was prompted by a 

design review that revealed insufficient 

measures were taken to ensure the 

correct locking of the attachments of the 

fuel quantity tank units (FQTUs) in each 

wing tank. When an FQTU becomes 

loose, this could lead to insufficient 

clearance between the FQTU and the 

adjacent tank structure or other metal 

parts, and under certain conditions, 

create an ignition source inside the wing 

fuel vapor space. This proposed AD 

would require modifying the FQTUs by 

applying sealant to cover the nuts, 

washers, and stud ends at the FQTU 

attachments in each main wing tank. 

This proposed AD would also require 


tkelley on DSK3SPTVN1PROD with PROPOSALS