Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules 10535 

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– 

2016–3700; Directorate Identifier 2015– 

NM–171–AD. 

(a) Comments Due Date 

We must receive comments by April 15, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 757–200 and –200CB, series 

airplanes, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder (DAH) indicating 

that the lap splices at stringer (S)–14R, lower 

fastener row, are subject to widespread 

fatigue damage (WFD). We are issuing this 

AD to detect and correct cracking of the 

fuselage skin lap splice. Such cracking could 

result in reduced structural integrity of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Initial Inspection 

At the applicable time specified in 

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

Alert Service Bulletin 757–53A0102, dated 

October 8, 2015, except as required by 

paragraph (h) of this AD: Do an external dual 

frequency eddy current inspection or internal 

high frequency eddy current inspection for 

cracking of the lap splice, inner skin lower 

fastener row, at S–14R, station (STA) 440 

through STA 540, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 757–53A0102, dated October 

8, 2015. Repeat either inspection thereafter at 

the time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 757–53A0102, dated October 8, 

2015. 

(h) Service Information Exceptions 

(1) Where Boeing Alert Service Bulletin 

757–53A0102, dated October 8, 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) The Condition column of paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 757–53A0102, dated October 8, 

2015, refers to total flight cycles and total 

flight hours ‘‘as of the original issue date of 

this service bulletin.’’ This AD, however, 

applies to the airplanes with the specified 

total flight cycles or total flight hours as of 

the effective date of this AD. 

(i) Repair 

If any crack is found during any inspection 

required by this AD, before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 (k) of this AD. Information may be 

emailed to: 9-ANM-LAACO-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, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes ODA that has been 

authorized by the Manager, Los Angeles 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) Except as required by paragraph (h) of 

this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (j)(4)(i) and (j)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. 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. 

(k) Related Information 

(1) For more information about this AD, 

contact Eric Schrieber, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles ACO, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; phone: 

562–627–5348; fax: 562–627–5210; email: 

eric.schrieber@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; telephone: 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 February 

15, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–03695 Filed 2–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–3987; Directorate 

Identifier 2015–NM–165–AD] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation 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 

Dassault Aviation Model FALCON 7X 

airplanes. This proposed AD was 

prompted by a report of improperly 

drilled bores, located on upper and 

lower stiffener joints to the web at a 

certain frame. This proposed AD would 

require a one-time inspection of the 

bores, and repair if necessary. We are 

proposing this AD to detect and correct 

an unsatisfactory bore that can 

adversely affect the structural integrity 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 15, 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. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
10536 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules 

• 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 NPRM, contact Dassault Falcon Jet 

Corporation, Teterboro Airport, P.O. 

Box 2000, South Hackensack, NJ 07606; 

telephone: 201–440–6700; Internet: 

http://www.dassaultfalcon.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–2016– 

3987; 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 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–2016–3987; Directorate Identifier 

2015–NM–165–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 Airworthiness 

Directive 2015–0204, dated October 8, 

2015, (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Dassault 

Aviation FALCON 7X airplanes. The 

MCAI states: 

On the assembly line of Falcon 7X 

airplanes, defects were detected on left hand 

and right hand engine pylons. A quality 

review revealed that bores located on upper 

and lower stiffener joints to the web at pylon 

Frame 41 were improperly drilled. Fettlings 

of borings, for fixing diameter 4 mm and 5 

mm, were found ovalized, too deep and 

having irregular surface qualities under the 

head of fixing. Dassault Aviation identified 

the individual airplanes that are potentially 

affected by this production deficiency. 

This condition, if not detected and 

corrected, would adversely affect the 

structural integrity of the airplane. 

To address this potential unsafe condition 

Dassault Aviation published Service Bulletin 

(SB) 7X–346 to provide corrective action 

instructions. 

For the reasons described above, this 

[EASA] AD requires a one-time [detailed] 

visual [and rototest] inspection for 

unsatisfactory bores and, depending on 

findings, repair of affected stiffener bores. 

A bore is not satisfactory if it has any 

surface defects greater than or equal to 

0.5 mm or if any chamfer dimension or 

edge distance value is not within the 

dimensions specified in Dassault 

Aviation Service Bulletin 7X–346, dated 

April 24, 2015. 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–2016–3987. 

Related Service Information Under 

1 CFR Part 51 

Dassault Aviation has issued Dassault 

Service Bulletin 7X–346 dated April 24, 

2015. The service information describes 

procedures for a one-time inspection of 

the bores on stiffeners at Frame 41 on 

the engine pylons, and repair if 

necessary. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

affects 55 airplanes of U.S. registry. 

We also estimate that it would take 

about 66 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $308,550, or $5,610 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 20 work-hours and require parts 

costing $149, for a cost of $1,849 per 

product. We have no way of 

determining the number of aircraft that 

might need this action. 

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 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules 10537 

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): 

Dassault Aviation: Docket No. FAA–2016– 

3987; Directorate Identifier 2015–NM– 

165–AD. 

(a) Comments Due Date 

We must receive comments by April 15, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Dassault Aviation 

Model FALCON 7X airplanes, certificated in 

any category, manufacturer serial numbers 1 

through 221 inclusive, except serial numbers 

182 and 220. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of 

improperly drilled bores, located on upper 

and lower stiffener joints to the web at a 

certain frame. We are issuing this AD to 

detect and correct an unsatisfactory bore that 

can adversely affect the structural integrity of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspect Bores 

Within 4,000 flight cycles or 98 months, 

whichever occurs first since date of issuance 

of the original airworthiness certificate or 

date of issuance of the original export 

certificate of airworthiness, do a detailed 

visual and rototest inspection of the bores, 

located on upper and lower stiffener joints to 

the web at pylon Frame 41, to determine if 

the bores are not satisfactory, in accordance 

with the Accomplishment Instructions of 

Dassault Service Bulletin 7X–346, dated 

April 24, 2015. 

(h) Repair 

If, during the inspection required by 

paragraph (g) of this AD, it is determined that 

any bore is not satisfactory: Before further 

flight, repair affected bores, in accordance 

with the Accomplishment Instructions of 

Dassault Service Bulletin 7X–346, dated 

April 24, 2015, except as required by 

paragraph (i) of this AD. 

(i) Exceptions 

Where the Dassault Service Bulletin 7X– 

346, dated April 24, 2015, specifies to contact 

Dassault Aviation: Before further flight, 

repair using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA); or 

Dassault Aviation’s EASA Design 

Organization Approval (DOA). 

(j) 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: 

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 

EASA; or Dassault Aviation’s EASA 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) EASA AD 

2015–0204, dated October 8, 2015, for related 

information. This MCAI may be found on the 

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

searching for and locating Docket No. FAA– 

2016–3987. 

(2) For service information identified in 

this AD, contact Dassault Falcon Jet 

Corporation, Teterboro Airport, P.O. Box 

2000, South Hackensack, NJ 07606; 

telephone: 201–440–6700; Internet: http://

www.dassaultfalcon.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 February 

19, 2016. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–04295 Filed 2–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–3986; Directorate 

Identifier 2015–NM–147–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 747–400, 

747–400D, and 747–400F series 

airplanes. This proposed AD was 

prompted by a determination that a 

certain fastener type in the fuel tank 

walls has insufficient bond to the 

structure, and an electrical wiring short 

could cause arcing to occur at the ends 

of fasteners in the fuel tanks. This 

proposed AD would require the 

installation of new clamps and 

polytetrafluoroethylene (TFE) sleeves on 

the wire bundles of the front spars and 

rear spars of the wings. This proposed 

AD would also require inspecting the 

existing TFE sleeves under the wire 

bundle clamps for correct installation, 

and replacement if necessary. We are 

proposing this AD to prevent potential 

ignition sources in the fuel tank in the 

event of a lightning strike or highpowered short circuit, and consequent 

fire or explosion. 


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