68392 Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules 

date of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(l) NWW Modification for Certain Airplanes 

For airplanes identified in Boeing Alert 

Service Bulletin 747–53A2808, dated 

November 30, 2012: At the applicable time 

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

Boeing Alert Service Bulletin 747–53A2808, 

dated November 30, 2012, or within 57 

months after December 11, 2006 (the effective 

date of AD 2006–22–15, Amendment 39– 

14812 (71 FR 64884, November 6, 2006)), 

whichever occurs later, replace the left side, 

right side, and top panels of the NWW, as 

applicable, with new panels; in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2808, 

dated November 30, 2012. Concurrently with 

doing the replacement specified in this 

paragraph, do a detailed inspection for cracks 

of the attaching structural elements that were 

common to the removed top, left-side, and 

right-side panels of the NWW, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2808, 

dated November 30, 2012. If any crack is 

found, before further flight, repair the 

cracking using a method approved in 

accordance with the procedures specified in 

paragraph (p) of this AD. 

(m) Repetitive Post-Modification Inspections 

for Certain Airplanes 

For airplanes on which the replacement 

specified in paragraph (l) has been done: At 

the applicable time specified in paragraph 

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

Bulletin 747–53A2808, dated November 30, 

2012, do the actions specified in paragraphs 

(l)(1), (l)(2), and (l)(3) of this AD. If any crack 

is found: Before further flight, repair the 

cracking using a method approved in 

accordance with the procedures specified in 

paragraph (p) of this AD. Repeat the 

inspections specified in paragraphs (m)(1), 

(m)(2), and (m)(3) of this AD thereafter at the 

applicable intervals specified in paragraph 

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

Bulletin 747–53A2808, dated November 30, 

2012. 

(1) Do an external detailed inspection for 

cracks in the side panel webs, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2808, 

dated November 30, 2012. 

(2) Do an internal detailed inspection and 

HFEC inspection for cracks in the top and 

side panel stiffeners, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2808, dated 

November 30, 2012. 

(3) Do an external detailed inspection for 

cracks in the top panel web, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2808, 

dated November 30, 2012. 

(n) Terminating Action 

Replacing the left side, right side, and top 

panels of the NWW with new panels as 

specified in paragraph (i) or (l) of this AD 

terminates the inspections required by 

paragraph (g) of this AD. 

(o) Credit for Previous Actions 

(1) This paragraph restates the credit given 

in paragraph (k) of AD 2006–22–15, 

Amendment 39–14812 (71 FR 64884, 

November 6, 2006). 

(i) This paragraph provides credit for the 

actions required by paragraph (g)(1) of this 

AD, if those actions were performed before 

January 27, 2005 (the effective date of AD 

2005–09–02, Amendment 39–14070 (70 FR 

21141, April 25, 2005); corrected on May 25, 

2005 (70 FR 29940)), using Boeing Alert 

Service Bulletin 747–53A2465, dated April 5, 

2001, which is not incorporated by reference 

in this AD. 

(ii) This paragraph provides credit for 

actions required by paragraphs (g)(1) and 

(g)(2) of this AD, if those inspections were 

performed before December 11, 2006 (the 

effective date of AD 2006–22–15, 

Amendment 39–14812 (71 FR 64884, 

November 6, 2006)), using a service bulletin 

identified in paragraph (o)(1)(ii)(A), 

(o)(1)(ii)(B), or (o)(1)(ii)(C) of this AD, which 

are not incorporated by reference in this AD. 

(A) Boeing Service Bulletin 747–53A2465, 

Revision 1, dated October 16, 2003. 

(B) Boeing Alert Service Bulletin 747– 

53A2465, Revision 2, dated November 11, 

2004. 

(C) Boeing Alert Service Bulletin 747– 

53A2465, Revision 3, dated December 23, 

2004. 

(2) This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Service 

Bulletin 747–53A2465, Revision 4, dated 

February 25, 2004, which is not incorporated 

by reference in this AD. 

(3) This paragraph provides credit for the 

actions required by paragraphs (i) and (j) of 

this AD, if those actions were performed 

before the effective date of this AD, using 

Boeing Service Bulletin 747–53A2562, 

Revision 1, dated July 28, 2005; or Boeing 

Service Bulletin 747–53A2562, Revision 2, 

dated May 31, 2007; which are not 

incorporated by reference in this AD. 

(p) 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 (p)(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 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) AMOCs approved for AD 2006–22–15, 

Amendment 39–14812 (71 FR 64884, 

November 6, 2006), are approved as AMOCs 

for the corresponding provisions of this AD. 

(5) AMOCs approved for paragraph (o) of 

AD 2006–22–15, Amendment 39–14812 (71 

FR 64884, November 6, 2006), are approved 

as AMOCs for the corresponding provisions 

of paragraph (l) of this AD. 

(q) Related Information 

(1) For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6432; fax: 425–917–6590; 

email: Bill.Ashforth@faa.gov. 

(2) For service information identified in 

this AD, 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 

November 6, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–27066 Filed 11–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0657; Directorate 

Identifier 2014–NM–058–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 2000, 

FALCON 2000EX, MYSTERE–FALCON 

900, and FALCON 900EX airplanes. 

This proposed AD was prompted by 

reports of a co-pilot sliding aft on his 

seat during take-off at rotation. This 

proposed AD would require 

replacement of certain springs installed 

on the pilot and co-pilot seats. We are 

proposing this AD to prevent fatigue 

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Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules 68393 

wear, which, if not corrected, could 

cause the seat to slide and the pilot or 

co-pilot to lose contact with the 

controls, leading to an inadvertent input 

on the flight control commands during 

take-off or climb, possibly resulting in 

loss of control of the airplane. 

DATES: We must receive comments on 

this proposed AD by January 2, 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 Dassault 

Falcon Jet, P.O. Box 2000, South 

Hackensack, NJ 07606; telephone 201– 

440–6700; Internet http://www.dassault

falcon.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–2014– 

0657; 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, 

Washington 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–2014–0657; Directorate Identifier 

2014–NM–058–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 

Community, has issued EASA 

Airworthiness Directive 2014–0061, 

dated March 11, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Dassault Aviation Model 

FALCON 2000, FALCON 2000EX, 

MYSTERE–FALCON 900, and FALCON 

900EX airplanes. The MCAI states: 

During take-off at rotation, a co-pilot 

reported to slide aft on his seat. 

The results of the investigations concluded 

that one spring of the seat locking system was 

broken and the other was weak. The root 

cause was determined to be fatigue wear. As 

springs accumulate cycles in service, they 

become increasingly exposed to the risk of 

unnoticed degradation or rupture. 

This condition, if not corrected, could 

cause the pilot or the co-pilot to lose contact 

with the controls, leading to an inadvertent 

input on the flight control commands during 

take-off or climb, possibly resulting in loss of 

control of the aeroplane. 

To address this unsafe condition, it was 

decided to require replacement of the 

affected seat springs for older aeroplanes and 

for newer aeroplanes; this task has been 

embodied in the aeroplane maintenance 

manual. 

For the reasons described above, this 

[EASA] AD requires replacement of the 

springs installed on the pilot and co-pilot 

seats with serviceable springs. 

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–2014– 

0657. 

Relevant Service Information 

Dassault Aviation has issued the 

following service bulletins. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

• Dassault Service Bulletin F900–429, 

Revision 1, also referred to as 429–R1, 

dated July 13, 2012. 

• Dassault Service Bulletin F900EX– 

446, Revision 1, also referred to as 446– 

R1, dated July 13, 2012. 

• Dassault Service Bulletin F2000– 

401, Revision 1, also referred to as 401– 

R1, dated July 13, 2012. 

• Dassault Service Bulletin F2000EX– 

267, Revision 1, also referred to as 267– 

R1, dated July 13, 2012. 

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. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

Although the MCAI does not require 

repetitive replacement of the pilot seat 

springs, this AD requires repetitive 

replacement of the pilot seat springs at 

intervals not to exceed 78 months or 

3,750 flight cycles, whichever occurs 

first. This difference has been 

coordinated with EASA. Also, we have 

been advised that EASA plans to revise 

the MCAI. 

Costs of Compliance 

We estimate that this proposed AD 

affects 528 airplanes of U.S. registry. 

We also estimate that it would take 

about 2 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 $83 per product. 

Based on these figures, we estimate the 

cost of this proposed AD on U.S. 

operators to be $133,584, or $253 per 

product. 

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. 

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68394 Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules 

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. Amend § 39.13 by adding the 

following new airworthiness directive 

(AD): 

Dassault Aviation: Docket No. FAA–2014– 

0657; Directorate Identifier 2014–NM– 

058–AD. 

(a) Comments Due Date 

We must receive comments by January 2, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) 

of this AD, certificated in any category, 

equipped with SICMA 132-series or 142- 

series pilot and co-pilot seats. 

(1) Dassault Aviation Model FALCON 2000 

airplanes 

(2) Dassault Aviation Model FALCON 

2000EX airplanes 

(3) Dassault Aviation Model MYSTERE– 

FALCON 900 airplanes 

(4) Dassault Aviation Model FALCON 

900EX airplanes 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/Furnishings. 

(e) Reason 

This AD was prompted by reports of a copilot sliding aft on his seat during take-off at 

rotation. We are issuing this AD to prevent 

fatigue wear, which, if not corrected, could 

cause the seat to slide and the pilot or copilot to lose contact with the controls, 

leading to an inadvertent input on the flight 

control commands during take-off or climb, 

possibly resulting in loss of control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement 

For airplanes that have accumulated more 

than 3,750 total flight cycles or have 

exceeded 74 months since the airplane’s first 

flight as of the effective date of this AD. 

Within 9 months after the effective date of 

this AD, replace each spring having part 

number (P/N) 132100–19 and P/N 147100–19 

installed on the pilot and co-pilot seats with 

a spring as specified in, and in accordance 

with, the Accomplishment Instructions of the 

service information identified in paragraph 

(g)(1), (g)(2), (g)(3), or (g)(4) of this AD, as 

applicable. Repeat the replacement thereafter 

at intervals not to exceed 78 months or 3,750 

flight cycles, whichever occurs first. 

(1) Dassault Service Bulletin F900–429, 

Revision 1, also referred to as 429–R1, dated 

July 13, 2012. 

(2) Dassault Service Bulletin F900EX–446, 

Revision 1, also referred to as 446–R1, dated 

July 13, 2012. 

(3) Dassault Service Bulletin F2000–401, 

Revision 1, also referred to as 401–R1, dated 

July 13, 2012. 

(4) Dassault Service Bulletin F2000EX–267, 

Revision 1, also referred to as 267–R1, dated 

July 13, 2012. 

(h) Parts Installation Limitation 

As of the effective date of this AD, 

installation of a spring having P/N 147100– 

19 on any airplane is allowed, provided that 

the spring is new. 

(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: 

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 Dassault Aviation’s EASA Design 

Organization Approval (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) European 

Aviation Safety Agency Airworthiness 

Directive 2014–0061, dated March 11, 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–2014–0657. 

(2) For service information identified in 

this AD, contact Dassault Falcon Jet, 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 

November 5, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–27068 Filed 11–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

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