3042 Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 

(n) New Terminating Modification 

Within 6,600 flight hours or 36 months, 

whichever occurs first after the effective date 

of this AD: Modify the airplane by increasing 

the clearance between the left and right MLG 

fairings and the left and right MLG doors; 

and do all applicable related investigative 

and corrective actions; in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 670BA–32–040, 

Revision E, dated November 13, 2014, except 

as provided by paragraph (o) of this AD. Do 

all applicable related investigative and 

corrective actions before further flight. If an 

MLG door has been removed, the 

modification may be delayed until the MLG 

door is re-installed in accordance with the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A670BA–32–030, 

Revision D, dated August 6, 2013. 

Accomplishing this modification terminates 

the requirements of paragraphs (g) through 

(m) of this AD for that MLG door. 

(o) Exceptions to Bombardier Service 

Bulletins 

Where Bombardier Alert Service Bulletin 

A670BA–32–030, Revision D, dated August 

6, 2013; and Bombardier Service Bulletin 

670BA–32–040, Revision E, dated November 

14, 2014; specify to contact the Bombardier 

Customer Response Center for an analysis or 

to get an approved disposition, repair using 

a method approved by the Manager, New 

York ACO, ANE–170, FAA; or TCCA; or 

Bombardier, Inc.’s TCCA DAO. 

(p) Credit for Previous Actions 

(1) This paragraph restates the provisions 

of paragraph (l) of AD 2010–23–19, 

Amendment 39–16508 (75 FR 68695, 

November 9, 2010), with additional service 

information. This paragraph provides credit 

for the actions required by paragraph (g) of 

this AD, if those actions were performed 

before November 24, 2010 (the effective date 

of AD 2010–23–19) using Bombardier Alert 

Service Bulletin A670BA–32–030, dated 

October 18, 2010; or Bombardier Alert 

Service Bulletin A670BA–32–030, Revision 

A, dated October 22, 2010. 

(2) This paragraph provides credit for the 

corresponding actions required by 

paragraphs (g)(1), (g)(2), (g)(3)(i), (g)(3)(ii), (h), 

(j)(1), (k), (l), (m), and (n) of this AD, if those 

actions were performed before the effective 

date of this AD using the service bulletins 

specified in paragraph (p)(2)(i), (p)(2)(ii), or 

(p)(2)(iii) of this AD. 

(i) Bombardier Alert Service Bulletin 

A670BA–32–030, Revision A, dated October 

22, 2010. 

(ii) Bombardier Alert Service Bulletin 

A670BA–32–030, Revision B, dated 

November 3, 2011. 

(iii) Bombardier Alert Service Bulletin 

A670BA–32–030, Revision C, dated March 

13, 2013. 

(3) This paragraph provides credit for the 

corresponding actions required by paragraph 

(n) of this AD, if those actions were 

performed before the effective date of this AD 

using the service information specified in 

paragraph (p)(3)(i), (p)(3)(ii), (p)(3)(iii), or 

(p)(3)(iv) of this AD. 

(i) Bombardier Service Bulletin 670BA–32– 

040, Revision A, dated March 13, 2013. 

(i) Bombardier Service Bulletin 670BA–32– 

040, Revision B, dated August 6, 2013. 

(iii) Bombardier Service Bulletin 670BA– 

32–040, Revision C, dated November 1, 2013. 

(iv) Bombardier Service Bulletin 670BA– 

32–040, Revision D, dated July 2, 2014. 

(q) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO, 

ANE–170, 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 ACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

516–228–7300; fax 516–794–5531. 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: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, New York ACO, ANE–170, 

FAA; or TCCA; or Bombardier, Inc.’s TCCA 

DAO. If approved by the DAO, the approval 

must include the DAO-authorized signature. 

(r) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2010–36R1, 

dated July 18, 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–2015–8471. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.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. 

Issued in Renton, Washington, on January 

6, 2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00698 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–2015–8472; Directorate 

Identifier 2014–NM–106–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 a hot spot 

may develop in the main fuel tank 

under certain failure conditions of the 

solenoid of the level control pilot valve, 

the reed switch of the main tank 

overflow valve, the level float switch of 

the collector tank, or the solenoid of the 

main tank fueling shut-off valve. This 

proposed AD would require installing 

fuses in the wiring of the solenoid of the 

level control pilot valve, the reed switch 

of the main tank overflow valve, the 

level float switch of the collector tank, 

and the solenoid of the main tank 

fueling shut-off valve, as applicable. 

This proposed AD would also require 

accomplishing concurrent actions 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 main 

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., 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 3043 

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– 

8472; 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–2015–8472; Directorate Identifier 

2014–NM–106–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 2014–0107, dated May 7, 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, under certain 

failure conditions of the solenoid of the level 

control pilot valve, the main tank overflow 

valve reed switch, the collector tank level 

float switch or the main tank fuelling shutoff valve solenoid, a hot spot may develop in 

the tank. 

This condition, if not corrected, could 

create an ignition source in the main tank 

vapour space, possibly resulting in a fuel 

tank explosion and consequent loss of the 

aeroplane. 

To address this potential unsafe condition, 

Fokker Services developed a modification to 

the wiring (installation of fuses) of the 

affected components. 

For the reasons described above, this AD 

requires the installation of fuses in the wiring 

of the affected components [the solenoid of 

the level control pilot valve, the reed switch 

of the main tank overflow valve, the level 

float switch of the collector tank, and the 

solenoid of the main tank fuelling shut-off 

valve] and, subsequently, the implementation 

of the associated Critical Design 

Configuration Control Limitations (CDCCL) 

items [and revision of the maintenance or 

inspection program]. 

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– 

8472. 

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. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
3044 Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following service 

information. 

• Fokker Service Bulletin SBF28–28– 

049, Revision 2, dated November 3, 

2014, including Fokker Drawing 

W57273, Sheet 002, Issue C, undated, 

Fokker Drawing W58048, Sheet 1, 

undated, and Fokker Manual Change 

Notification MCNM–F28–035, Rev 1, 

dated January 9, 2014. This service 

information describes procedures for 

installing fuses packed in jiffy junctions 

in the collector tank. 

• Fokker Proforma Service Bulletin 

SBF28–28–056, dated January 9, 2014, 

including Appendix SBF28–28–056/

APP01, dated July 15, 2014. This service 

information describes procedures for 

installing fuses in the wiring of the 

solenoid of the level control pilot valve, 

the reed switch of the main tank 

overflow valve, the level float switch of 

the collector tank, and the solenoid of 

the main tank fueling shut-off valve. 

This service information also describes 

certain CDCCLs. 

• Fokker Service Bulletin SBF28–28– 

051, Revision 2, dated November 3, 

2014, including Drawing W57231, 

Sheets 010 and 011, Issue K, undated; 

Drawing W58048, Sheet 2, dated April 

29, 2010; and Manual Change 

Notification—Maintenance Document 

MCNM–F28–034 Rev 1, dated January 9, 

2014. This service information describes 

procedures for reworking the wiring and 

installing fuses packed in jiffy junctions 

in the power supply wire of the 

solenoid in the left and right level 

control pilot valves. 

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 (k)(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 $5,320 per 

product. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $35,525, or $7,105, 

or 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, 

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– 

2015–8472; Directorate Identifier 2014– 

NM–106–AD. 

(a) Comments Due Date 

We must receive comments by March 7, 

2016. 

(b) Affected ADs 

This AD affects AD 2011–17–03, 

Amendment 39–16767 (76 FR 50115, August 

12, 2011); and AD 2011–21–01, Amendment 

39–16824 (76 FR 63156, October 12, 2011). 

(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, 

which revealed that a hot spot may develop 

in the main fuel tank under certain failure 

conditions of the solenoid of the level control 

pilot valve, the reed switch of the main tank 

overflow valve, the level float switch of the 

collector tank, or the solenoid of the main 

tank fueling shut-off valve. We are issuing 

this AD to prevent an ignition source in the 

main fuel tank vapor space, which could 

result in a fuel tank explosion and 

consequent loss of the airplane. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 3045 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification of Main Fuel Tank Wiring 

Within 24 months after the effective date 

of this AD, install fuses in the wiring of the 

solenoid of the level control pilot valve, the 

reed switch of the main tank overflow valve, 

the level float switch of the collector tank, 

and the solenoid of the main tank fueling 

shut-off valve, as applicable, in accordance 

with the Accomplishment Instructions of 

Fokker Services Proforma Service Bulletin 

SBF28–28–056, dated January 9, 2014, 

including Appendix SBF28–28–056/APP01, 

dated July 15, 2014. 

(h) Concurrent Requirements 

Prior to or concurrently with 

accomplishing the requirements of paragraph 

(g) of this AD, do the actions specified in 

paragraphs (h)(1) and (h)(2) of this AD. 

(1) Install fuses packed in jiffy junctions 

(i.e., crimped wire in-line junction device(s)), 

in accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF28–28–049, Revision 2, dated November 

3, 2014, including Fokker Drawing W57273, 

Sheet 002, Issue C, undated, Fokker Drawing 

W58048, Sheet 1, undated, and Fokker 

Manual Change Notification MCNM–F28– 

035, Rev 1, dated January 9, 2014. 

Accomplishment of the actions in this 

paragraph terminates the requirement of 

paragraph (g) of AD 2011–17–03, 

Amendment 39–16767 (76 FR 50115, August 

12, 2011). 

Note 1 to paragraph (h)(1) of this AD: 

Accomplishment of this action is required by 

AD 2011–17–03, Amendment 39–16767 (76 

FR 50115, August 12, 2011). 

(2) Rework the wiring and install fuses 

packed in jiffy junctions in the power supply 

wire of the solenoid in the left and right level 

control pilot valve, in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF28–28–051, Revision 2, 

dated November 3, 2014, including Drawing 

W57231, Sheets 010 and 011, Issue K, 

undated; Drawing W58048, Sheet 2, dated 

April 29, 2010; and Manual Change 

Notification—Maintenance Document 

MCNM–F28–034, Rev 1, dated January 9, 

2014. Accomplishment of the actions in this 

paragraph terminates the requirement of 

paragraph (g) of AD 2011–21–01, 

Amendment 39–16824 (76 FR 63156, October 

12, 2011), for the actions specified in the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF28–28–051, Revision 2, 

dated November 3, 2014, including Drawing 

W57231, Sheets 010 and 011, Issue K, 

undated; Drawing W58048, Sheet 2, dated 

April 29, 2010; and Manual Change 

Notification—Maintenance Document 

MCNM–F28–034, Rev 1, dated January 9, 

2014, only. 

Note 2 to paragraph (h)(2) of this AD: 

Accomplishment of this action is required by 

AD 2011–21–01, Amendment 39–16824 (76 

FR 63156, October 12, 2011). 

(i) 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 critical 

design configuration control limitations 

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

Fokker Services Proforma Service Bulletin 

SBF28–28–056, dated January 9, 2014, 

including Appendix SBF28–28–056/APP01, 

dated July 15, 2014. 

(j) No Alternative CDCCLs 

After accomplishing the revision required 

by paragraph (i) of this AD, no alternative 

CDCCLs may be used unless the CDCCLs are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (k)(1) of 

this AD. 

(k) 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. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2014–0107, dated May 7, 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–2015–8472. 

(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 

6, 2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00700 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–2015–8470; Directorate 

Identifier 2013–NM–199–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 95–21–09, 

for all Airbus Model A300 series 

airplanes, and Airbus Model A300 B4– 

600, B4–600R, and F4–600R series 

airplanes, and Model A300 C4–605R 

Variant F airplanes (collectively called 

Model A300–600 series airplanes). AD 

95–21–09 currently requires repetitive 

inspections for cracking of the No. 2 flap 

beams, and replacement of the flap 

beams, if necessary; and provides 

optional modifications for extending 

certain inspection thresholds, and an 

optional terminating modification for 

certain inspections. Since we issued AD 

95–21–09, we have determined that the 

compliance times must be reduced. This 

proposed AD would reduce the 

compliance times for inspections and 

also reduce the number of airplanes 

affected. We are proposing this AD to 

detect and correct cracking of the No. 2 

flap beams, which could result in 

rupture of the flap beams and reduced 

structural integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 7, 2016. 

ADDRESSES: You may send comments 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. 


tkelley on DSK3SPTVN1PROD with PROPOSALS