Federal Register / Vol. 80, No. 114 / Monday, June 15, 2015 / Proposed Rules 34103 

conclusively determined from that review. 

For any engine replaced as specified in the 

Airbus A318/A319/A320/A321 Aircraft 

Maintenance Manual (AMM), Task 71–00– 

00–400–040–A01, ‘‘Installation of the Power 

Plant with Engine Positioner TWW 75E,’’ 

dated May 2013: Within 6 months or 1,500 

flight cycles, whichever occurs first after the 

effective date of this AD, re-torque the 4 aft 

mount pylon bolts using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’ EASA Design 

Organization Approval (DOA). 

Note 1 to paragraph (g) of this AD: 

Additional guidance for the re-torque can be 

found in Airbus A318/A319/A320/A321 

AMM Temporary Revision 71–030, dated 

March 14, 2014, or Airbus A318/A319/A320/ 

A321 AMM Task 71–00–00–400–040–A01, 

‘‘Installation of the Power Plant with Engine 

Positioner TWW 75E,’’ dated May 2014. 

(h) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install a CFM56–5 engine, on any 

airplane, unless the engine is installed in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

71–1063, including Appendix 01, dated 

August 13, 2014. 

(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 EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0258, dated 

November 28, 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–2015–1429. 

(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 June 3, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–14228 Filed 6–12–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1428; Directorate 

Identifier 2015–NM–026–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 777–200 

and –300 series airplanes. This 

proposed AD was prompted by reports 

of fatigue cracking of a certain chord of 

the pivot bulkhead. This proposed AD 

would require repetitive inspections for 

cracking of the left side and right side 

forward outer chords of the pivot 

bulkhead, and related investigative and 

corrective actions if necessary. This 

proposed AD provides a modification of 

the pivot bulkhead, which would 

terminate the repetitive inspections. We 

are proposing this AD to detect and 

correct fatigue cracking of the outer 

flanges of the left and right side forward 

outer chords of the pivot bulkhead, 

which could result in a severed forward 

outer chord and consequent loss of 

horizontal stabilizer control. 

DATES: We must receive comments on 

this proposed AD by July 30, 2015. 

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 proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

phone: 206–544–5000, extension 1; fax: 

206–766–5680; Internet https://

www.myboeingfleet.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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1428. 

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– 

1428; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Narinder Luthra, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6513; 

fax: 425–917–6590; email: 

narinder.luthra@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–1428; Directorate Identifier 2015– 

NM–026–AD’’ at the beginning of your 

comments. We specifically invite 


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34104 Federal Register / Vol. 80, No. 114 / Monday, June 15, 2015 / Proposed Rules 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We received reports of fatigue 

cracking of the forward outer chord of 

the STA 2370 pivot bulkhead. Cracks in 

the forward outer chords of the STA 

2370 pivot bulkhead that are not found 

and repaired can become large and 

result in a severed forward outer chord. 

The cracks were caused by a stress 

concentration, which is generated at the 

transition radius of the forward outer 

flange of the chord prior to the chord 

splice at the upper longeron. Since the 

horizontal stabilizer is attached to the 

STA 2370 bulkhead at two pivot 

locations, fatigue cracking of the outer 

flanges of the left and right side forward 

outer chords of the STA 2370 pivot 

bulkhead, if not corrected, could result 

in a severed forward outer chord and 

consequent loss of horizontal stabilizer 

control. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following Boeing 

service information. 

• Boeing Alert Service Bulletin 777– 

53A0075, dated January 14, 2015, 

describes procedures for repetitive 

detailed and high frequency eddy 

current (HFEC) inspections for cracking 

of the outer flanges of the left and right 

side forward outer chords of the STA 

2370 pivot bulkhead, repetitive postrepair inspections for certain airplanes, 

and related investigative and corrective 

actions. 

• Boeing Service Bulletin 777–53– 

0076, dated January 14, 2015, describes 

procedures for a modification of the 

STA 2370 pivot bulkhead by replacing 

the left and right side forward outer 

chords and upper splice angles, and 

related investigative and corrective 

actions. 

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 of 

this NPRM. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between this Proposed AD 

and the Service Information.’’ Refer to 

this service information for details on 

the procedures and compliance times. 

The phrase ‘‘related investigative 

actions’’ is used in this proposed AD. 

‘‘Related investigative actions’’ are 

follow-on actions that (1) are related to 

the primary actions, and (2) further 

investigate the nature of any condition 

found. Related investigative actions in 

an AD could include, for example, 

inspections. 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 

actions’’ are actions that correct or 

address any condition found. Corrective 

actions in an AD could include, for 

example, repairs. 

Explanation of ‘‘RC’’ Steps 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 steps in the service 

information are required for compliance 

with an AD. Differentiating these steps 

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 steps identified as RC 

(required for compliance) in any service 

information identified previously have a 

direct effect on detecting, preventing, 

resolving, or eliminating an identified 

unsafe condition. 

For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the following 

provisions apply: (1) 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, and an AMOC is required for any 

deviations to RC steps, including 

substeps and identified figures; and (2) 

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. 

Differences Between This Proposed AD 

and the Service Information 

The service bulletin specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

affects 60 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 

Inspections of left and right 

side pivot bulkhead forward 

chord.

Up to 15 work-hours × $85 

per hour = $1,275 per inspection cycle.

$0 Up to $1,275 per inspection 

cycle.

Up to $76,500 per inspection 

cycle. 

Post-Repair Inspections .......... Up to 11 work-hours × $85 

per hour = $935 per inspection cycle.

0 Up to $935 per inspection 

cycle.

Up to $56,100 per inspection 

cycle. 


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Federal Register / Vol. 80, No. 114 / Monday, June 15, 2015 / Proposed Rules 34105 

We estimate the following costs to do 

any necessary repairs and modifications 

that would be required based on the 

results of the proposed inspection. We 

have no way of determining the number 

of aircraft that might need these actions: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Small crack repair .......................................................... Up to 45 work-hours × $85 per hour = $3,825 per 

side.

(1) Up to $7,650. 

Modification of the STA 2370 Pivot Bulkhead (forward 

outer chord replacement).

Up to 137 work-hours × $85 per hour = $11,645 ........ $34,086 Up to $45,731. 

1We have received no definitive data that would enable us to provide parts cost estimates for the on-condition repair specified in this proposed 

AD. 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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): 

The Boeing Company: Docket No. FAA– 

2015–1428; Directorate Identifier 2015– 

NM–026–AD. 

(a) Comments Due Date 

We must receive comments by July 30, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200 and –300 series airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin 777–53A0075, 

dated January 14, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fatigue cracking of the forward outer chord of 

the station (STA) 2370 pivot bulkhead. We 

are issuing this AD to detect and correct 

fatigue cracking of the outer flanges of the left 

and right side forward outer chords of the 

STA 2370 pivot bulkhead, which could result 

in a severed forward outer chord and 

consequent loss of horizontal stabilizer 

control. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections and Corrective Actions 

At the times specified in table 1 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 777–53A0075, dated 

January 14, 2015, except as provided in 

paragraph (j)(1) of this AD: Do a detailed 

inspection and high frequency eddy current 

(HFEC) inspections for cracking of the left 

and right side forward outer chords of the 

STA 2370 pivot bulkhead, and do all 

applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–53A0075, dated January 

14, 2015, except as provided in paragraph 

(j)(2) of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. Repeat the inspections 

thereafter at the applicable intervals specified 

in table 1 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Alert Service Bulletin 777– 

53A0075, dated January 14, 2015, until the 

modification specified in paragraph (i) of this 

AD is done. 

(h) Post-Repair Inspections 

For airplanes on which a repair specified 

in Part 2 of the Accomplishment Instructions 

of Boeing Alert Service Bulletin 777– 

53A0075 has been done: At the times 

specified in table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 777–53A0075, dated January 14, 

2015, do a surface HFEC inspection, an openhole HFEC inspection, and a detailed 

inspection for cracking of the left side and 

right side forward outer chords of the STA 

2370 pivot bulkhead, and do all applicable 

related investigative and corrective actions, 

in accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–53A0075, dated January 

14, 2015, except as required by paragraph 

(j)(2) of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. Repeat the inspections 

thereafter at the applicable times specified in 

table 2 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 777–53A0075, 

dated January 14, 2015, until the 

modification specified in paragraph (i) of this 

AD is done. 


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(i) Terminating Action 

Modifying the STA 2370 pivot bulkhead by 

replacing the left and right side forward outer 

chords and upper splice angles, and doing all 

applicable related investigative and 

corrective actions, terminates the repetitive 

inspections required by paragraphs (g) and 

(h) of this AD for the modified location only. 

The modification must be done in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 777– 

53–0076, dated January 14, 2015, except as 

required by paragraph (j)(2) of this AD. 

(j) Exceptions to Service Bulletin 

Specifications 

(1) Where Boeing Alert Service Bulletin 

777–53A0075, dated January 14, 2015, 

specifies a compliance time ‘‘after the 

Original Issue date of this Service Bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) Although Boeing Alert Service Bulletin 

777–53A0075, dated January 14, 2015; and 

Boeing Service Bulletin 777–530076, dated 

January 14, 2015; specify to contact Boeing 

for appropriate action, and Boeing Alert 

Service Bulletin 777–53A0075, dated January 

14, 2015, specifies that action as ‘‘RC’’ 

(Required for Compliance), this AD requires 

repair before further flight using a method 

approved in accordance with the procedures 

specified in paragraph (k) of this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 ACO, send it to the 

attention of the person identified in 

paragraph (l)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) Except as required by paragraph (j)(2) 

of this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (k)(4)(i) and (k)(4)(ii) 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. 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. 

(l) Related Information 

(1) For more information about this AD, 

contact Narinder Luthra, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6513; fax: 425– 

917–6590; email: narinder.luthra@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; phone: 206–544– 

5000, extension 1; fax: 206–766–5680; 

Internet https://www.myboeingfleet.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 June 2, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–14231 Filed 6–12–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1982; Directorate 

Identifier 2014–NM–108–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, which revealed that no 

controlled bonding provisions are 

present on a number of critical locations 

outside the fuel tank. This proposed AD 

would require installing additional and 

improved fuel system bonding 

provisions, and revising the airplane 

maintenance or inspection program, as 

applicable, by incorporating fuel 

airworthiness limitation items and 

critical design configuration control 

limitations. 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 July 30, 2015. 

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– 

1982; 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: 


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