Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 3051 

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. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2013–0234R2, dated October 7, 2013, 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–2015–8470. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 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 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 

6. 2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00634 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–2015–8467; Directorate 

Identifier 2014–NM–107–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 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. This proposed 

AD would require installing additional 

and improved bonding provisions in the 

fuel tanks and revising the airplane 

maintenance or inspection program, as 

applicable, by incorporating fuel 

airworthiness limitation items and 

critical design configuration control 

limitations (CDCCLs). We are proposing 

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. 

DATES: We must receive comments on 

this proposed AD 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 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 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–2015– 

8467; or in person at the Docket 

Operations office 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 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: 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. 

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–2015–8467; Directorate Identifier 

2014–NM–107–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0108, dated May 8, 2014 

(referred to after this the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for all Fokker Services B.V. 

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

4000 airplanes. The MCAI states: 

Prompted by an accident * * *, the 

Federal Aviation Administration (FAA) 

published Special Federal Aviation 

Regulation (SFAR) 88 [(66 FR 23086, May 7, 

2001)], and the Joint Aviation Authorities 

(JAA) published Interim Policy INT/POL/25/ 

12. 

The review conducted by Fokker Services 

on the Fokker F28 design, in response to 

these regulations, revealed that no controlled 

bonding provisions are present on a number 

of critical locations, inside the fuel tank or 

connected to the fuel tank wall. 

This condition, if not corrected, could 

create an ignition source in the fuel tank 

vapour space, possibly resulting in a fuel 

tank explosions and consequent loss of the 

aeroplane. 

To address this potential unsafe condition, 

Fokker Services developed a set of fuel tank 

bonding modifications. 

For the reasons described above, this 

[EASA] AD requires the Installation of 

additional and improved bonding provisions 

[and a revision of the maintenance or 

inspection program, as applicable]. These 

modifications require opening of the fuel 

tank access panels. 

More information on this subject can be 

found in Fokker Services All Operators 

Message AOF28.038#02. 

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–2015– 

8467. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
3052 Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 

Regulation No. 88 (‘‘SFAR 88,’’ 

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 (66 FR 

23086, May 7, 2001) requires certain 

type design (i.e., type certificate (TC) 

and supplemental type certificate (STC)) 

holders to substantiate that their fuel 

tank systems can prevent ignition 

sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 

and to develop design changes and 

maintenance procedures if their designs 

do not meet the new fuel tank safety 

standards. As explained in the preamble 

to the rule, we intended to adopt 

airworthiness directives to mandate any 

changes found necessary to address 

unsafe conditions identified as a result 

of these reviews. 

In evaluating these design reviews, we 

have established four criteria intended 

to define the unsafe conditions 

associated with fuel tank systems that 

require corrective actions. The 

percentage of operating time during 

which fuel tanks are exposed to 

flammable conditions is one of these 

criteria. The other three criteria address 

the failure types under evaluation: 

Single failures, single failures in 

combination with a latent condition(s), 

and in-service failure experience. For all 

four criteria, the evaluations included 

consideration of previous actions taken 

that may mitigate the need for further 

action. 

The Joint Aviation Authorities (JAA) 

has issued a regulation that is similar to 

SFAR 88 (66 FR 23086, May 7, 2001). 

(The JAA is an associated body of the 

European Civil Aviation Conference 

(ECAC) representing the civil aviation 

regulatory authorities of a number of 

European States who have agreed to cooperate in developing and 

implementing common safety regulatory 

standards and procedures.) Under this 

regulation, the JAA stated that all 

members of the ECAC that hold type 

certificates for transport category 

airplanes are required to conduct a 

design review against explosion risks. 

We have determined that the actions 

identified in this AD are necessary to 

reduce the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss of the airplane. 

Related Service Information Under 1 

CFR Part 51 

Fokker Services B.V. has issued 

Fokker Proforma Service Bulletin 

SBF28–28–058, dated January 9, 2014, 

including Appendix SBF28–28–058/

APP01, dated July 15, 2014. The service 

information describes procedures for 

installing improved bonding provisions 

for the transfer jet pumps, ventilation 

float valves, center tank overflow valves, 

and level control pilot valves wiring 

conduit, and applicable related 

investigative and corrective actions. 

Fokker Services B.V. has also issued 

Fokker Service Bulletin SBF28–28–050, 

Revision 3, dated December 11, 2014. 

The service information describes 

certain fuel airworthiness limitation 

items and critical design configuration 

control limitations. 

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 these same 

type designs. 

This AD requires revisions to certain 

operator maintenance documents to 

include new actions (e.g., inspections) 

and/or CDCCLs. Compliance with these 

actions and/or CDCCLs is required by 14 

CFR 91.403(c). For airplanes that have 

been previously modified, altered, or 

repaired in the areas addressed by this 

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 (j)(1) of this AD. The request 

should include a description of changes 

to the required actions that will ensure 

the continued operational safety of the 

airplane. 

Costs of Compliance 

We estimate that this proposed AD 

affects 5 airplanes of U.S. registry. 

We also estimate that it would take 

about 21 work-hours per product to 

comply with the basic requirements of 

this proposed AD. 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 proposed AD on U.S. 

operators to be $8,925, or $1,785 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); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 


tkelley on DSK3SPTVN1PROD with PROPOSALS
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