Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules 25249 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Fokker Services B.V.: Docket No. FAA– 

2015–0933; Directorate Identifier 2014– 

NM–098–AD. 

(a) Comments Due Date 

We must receive comments by June 18, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model F.27 Mark 200, 300, 400, 500, 600, and 

700 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 no controlled bonding 

provisions are present on a number of critical 

locations inside the fuel tank or connected to 

the fuel tank wall; and no anti-spray cover is 

installed on the fuel shut-off valve (FSOV) in 

both wings. We are issuing this AD to 

prevent an ignition source in the fuel tank 

vapor space, which could result in a fuel tank 

explosion and consequent loss of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Installation of Bonding Provisions and 

Anti-Spray Cover 

At the next scheduled opening of the fuel 

tanks after the effective date of this AD, but 

no later than 84 months after the effective 

date of this AD: Install additional bonding 

provisions at the applicable locations, and 

install an anti-spray cover on the FSOV in 

both wings, using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA. 

(h) Revision of Maintenance or Inspection 

Program 

Within 30 days after installing the bonding 

provisions and anti-spray cover specified in 

paragraph (g) of this AD: Revise the airplane 

maintenance or inspection program, as 

applicable, by incorporating fuel 

airworthiness limitation items and Critical 

Design Configuration Control Limitations 

(CDCCLs), using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA. 

(i) No Alternative Actions, Intervals, and/or 

CDCCLs 

After accomplishing the revision required 

by paragraph (h) of this AD, no alternative 

actions (e.g., inspections), intervals, or 

CDCCLs may be used unless the actions, 

intervals, or CDCCLs are approved as an 

alternative method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(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 425–227–1137. 

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 Fokker Services B.V.’s EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0099, dated 

April 30, 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– 

2015–0933. 

Issued in Renton, Washington, on April 17, 

2015. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–10180 Filed 5–1–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0937; Directorate 

Identifier 2014–NM–024–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) 2011–24– 

05, for certain Airbus Model A330–201, 

–202, –203, –223, –243, –301, –302, 

–303, –321, –322, –323, –341, –342, and 

–343 airplanes; and Model A340–200 

and –300 series airplanes. AD 2011–24– 

05 currently requires repetitive 

inspections for cracking of the hole(s) of 

the horizontal flange of the keel beam, 

and repair if necessary. Since we issued 

AD 2011–24–05, a determination was 

made that the rototest inspection and 

applicable corrective actions of a certain 

fastener hole were inadvertently omitted 

from the requirements in that AD. This 

proposed AD would change the 

inspection compliance times, and, for 

certain airplanes, would add a one-time 

ultrasonic inspection for cracking at a 

certain fastener hole. This proposed AD 

would also provide optional terminating 

action for the repetitive inspections. We 

are proposing this AD to detect and 

correct cracking of the fastener holes, 

which could result in rupture of the keel 

beam, and consequent reduced 

structural integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by June 18, 2015. 

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. 

• 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 Airbus SAS— 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.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://


tkelley on DSK3SPTVN1PROD with PROPOSALS
25250 Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules 

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0937; 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

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–2015–0937; Directorate Identifier 

2014–NM–024–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 

On November 7, 2011, we issued AD 

2011–24–05, Amendment 39–16869 (76 

FR 73496, November 29, 2011), for 

certain Airbus Model A330–201, –202, 

–203, –223, –243, –301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes; and Model A340–200 and 

–300 series airplanes. AD 2011–24–05 

requires actions intended to address the 

unsafe condition on the products listed 

above. 

Since we issued AD 2011–24–05, 

Amendment 39–16869 (76 FR 73496, 

November 29, 2011), the European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Union, has 

issued EASA Airworthiness Directive 

2014–0010R1, dated May 5, 2014 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

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

condition for certain Airbus Model 

A330–201, –202, –203, –223, –243, 

–301, –302, –303, –321, –322, –323, 

–341, –342, and –343 airplanes; and 

Model A340–200 and –300 series 

airplanes. The MCAI states: 

During A330 and A340 aeroplanes fatigue 

tests, cracks were detected on the RH [righthand] and LH [left-hand] sides between the 

crossing area of the keel beam fitting and the 

front spar of the Centre Wing Box (CWB). 

This condition, if not detected and 

corrected, could lead to keel beam rupture 

which would affect the area structural 

integrity of the area. 

Prompted by this potential unsafe 

condition, EASA issued AD 2006–0315 

[http://ad.easa.europa.eu/blob/easa_ad_

2006_0315.pdf/AD_2006-0315] (later revised 

to R1) to require repetitive special detailed 

inspections (SDI) [rotating probe inspection 

for cracking] on the horizontal flange of the 

keel beam in the area of first fastener hole aft 

of Frame (FR) 40 in order to maintain the 

structural integrity of the aeroplane. 

After that [EASA] AD was issued, EASA 

issued AD 2010–0024 [which corresponds to 

FAA AD 2011–24–05, Amendment 39–16869 

(76 FR 73496, November 29, 2011)], retaining 

the inspection requirements of EASA AD 

2006–0315R1 [http://ad.easa.europa.eu/blob/ 

easa_ad_2006_0315R1.pdf/AD_2006- 

0315R1], which was superseded, extending 

the applicability to aeroplanes with Airbus 

Mod 49202 embodied, and reducing the 

inspection thresholds and intervals. 

Since that [EASA] AD [2010–0024] was 

issued, a new fatigue and damage tolerance 

evaluation has been conducted by Airbus, 

which concluded that due to the aeroplane 

utilization, the current inspection threshold 

and intervals have to be modified. 

In addition, it was determined that the 

rototest inspection of fastener hole Nr 6, 

necessary to ensure that no crack was left 

unrepaired at the time of fastener hold cold 

working, was inadvertently not included in 

Revisions 01 and 02 of both Airbus Service 

Bulletin (SB) A330–57–3098 and A340–57– 

4106. 

Prompted by these findings, EASA issued 

AD 2014–0010 [http://ad.easa.europa.eu/

blob/easa_ad_2014-0010.pdf/AD_2014-0010], 

retaining the requirements of EASA AD 

2010–0024, which was superseded, and 

redefined the inspection thresholds and 

intervals [by reducing certain compliance 

times], and added a one-time ultrasonic 

inspection of fastener hold Nr 6 in the 

junction keel beam fitting at FR40 on both LH 

and RH side[s]. 

Following issuance of EASA AD 2014– 

0010, it was identified that there was a need 

for clarifications [of affected airplanes] 

* * *. 

The compliance times vary depending 

on airplane utilization and 

configuration. The earliest compliance 

time for the initial rotating probe 

inspections is the later of (1) before 

10,400 total flight cycles or 67,800 total 

flight hours, whichever occurs first; and 

(2) within 24 months or 14,590 flight 

cycles or 43,790 flight hours, whichever 

occurs first. The latest compliance time 

for the initial inspections is the later of 

(1) before 20,800 total flight cycles or 

67,900 total flight hours, whichever 

occurs first; and (2) within 24 months or 

21,180 flight cycles or 63,560 flight 

hours, whichever occurs first. The 

compliance times for the repetitive 

intervals range between 7,800 flight 

cycles or 50,900 flight hours and 10,700 

flight cycles or 35,200 flight hours. The 

compliance times for the one-time 

ultrasonic inspection are the latest of (1) 

21,000 flight cycles or 60,600 flight 

hours and within 2,400 flight cycles or 

24 months; or the latest of (2) 22,100 

flight cycles and 64,400 flight hours, or 

within 1,300 flight cycles or 24 months. 

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– 

0937. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. 

• Airbus Service Bulletin A330–57– 

3081, Revision 05, including Appendix 

01, dated November 13, 2012. 

• Airbus Service Bulletin A330–57– 

3090, dated June 15, 2011. 

• Airbus Service Bulletin A330–57– 

3098, dated August 30, 2007. 

• Airbus Service Bulletin A330–57– 

3098, Revision 02, June 15, 2011. 

• Airbus Service Bulletin A330–57– 

3098, Revision 03, including Appendix 

01, dated September 24, 2014. 

• Airbus Service Bulletin A330–57– 

3117, including Appendix 01, dated 

January 25, 2013. 

• Airbus Service Bulletin A340–57– 

4089, Revision 05, including Appendix 

01, dated November 13, 2012. 

• Airbus Service Bulletin A340–57– 

4098, Revision 01, dated June 15, 2011. 

• Airbus Service Bulletin A340–57– 

4106, dated August 30, 2007. 

• Airbus Service Bulletin A340–57– 

4106, Revision 02, including Appendix 

01, dated August 30, 2007. 

• Airbus Service Bulletin A340–57– 

4106, Revision 03, including Appendix 

01, dated September 24, 2012. 

• Airbus Service Bulletin A340–57– 

4126, including Appendix 01, dated 

January 25, 2013. 

This service information describes 

procedures for inspections for cracking 

of the hole(s) of the horizontal flange of 

the keel beam, and contacting the 

manufacturer for repair instructions. 

Additionally, this service information 

describes procedures for a one-time 

ultrasonic inspection for cracking at 

fastener hole ‘‘Nr 6,’’ and provides 


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Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules 25251 

optional terminating action for the 

repetitive inspections. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 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. 

Explanation of Compliance Time 

The compliance time for the 

modification specified in this proposed 

AD for addressing widespread fatigue 

damage (WFD) was established to 

ensure that discrepant structure is 

modified before WFD develops in 

airplanes. Standard inspection 

techniques cannot be relied on to detect 

WFD before it becomes a hazard to 

flight. We will not grant any extensions 

of the compliance time to complete any 

AD-mandated service bulletin related to 

WFD without extensive new data that 

would substantiate and clearly warrant 

such an extension. 

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 35 airplanes of U.S. registry. 

The actions that are required by AD 

2011–24–05, Amendment 39–16869 (76 

FR 73496, November 29, 2011), and 

retained in this proposed AD take about 

41 work-hours per product, at an 

average labor rate of $85 per work hour. 

Required parts cost about $191 per 

product. Based on these figures, the 

estimated cost of the actions that are 

required by AD 2011–24–05 is $3,676 

per product. 

We also estimate that it would take 

about 23 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 $68,425, or $1,955 per product. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this proposed AD. 

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 

removing Airworthiness Directive (AD) 

2011–24–05, Amendment 39–16869 (76 

FR 73496, November 29, 2011), and 

adding the following new AD: 

Airbus: Docket No. FAA–2015–0937; 

Directorate Identifier 2014–NM–024–AD. 

(a) Comments Due Date 

We must receive comments by June 18, 

2015. 

(b) Affected ADs 

This AD replaces AD 2011–24–05, 

Amendment 39–16869 (76 FR 73496, 

November 29, 2011). 

(c) Applicability 

(1) This AD applies to the airplanes 

identified in paragraphs (c)(1)(i) and (c)(1)(ii) 

of this AD, certificated in any category, 

except as provided by paragraph (c)(2) of this 

AD. 

(i) Airbus Model A330–201, –202, –203, 

–223, –243, –301, –302, –303, –321, –322, 

–323, –341, –342, and –343 airplanes, all 

serial numbers, except those on which 

Airbus modification 55306 or 55792 has been 

embodied in production. 

(ii) Airbus Model A340–211, –212, –213, 

–311, –312, and –313 airplanes, all serial 

numbers, except those on which Airbus 

modification 55306 or 55792 has been 

embodied in production. 

(2) This AD does not apply to Airbus 

Model A340–211, –212, –213, –311, –312, 

and –313 airplanes on which the repair 

specified in Airbus Repair Drawing 

R57115053, R57115051, or R57115047 

(installation of titanium doubler on both 

sides) has been accomplished. AD 2007–12– 

08, Amendment 39–15086 (72 FR 31171, 

June 6, 2007), applies to these airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports of cracks 

on the keel beam fitting and the front spar 

of the center wing box. This AD was also 

prompted by a determination that the rototest 

inspection and applicable corrective actions 

of fastener hole Nr 6 were inadvertently 

omitted from the requirements in AD 2011– 

24–05, Amendment 39–16869 (76 FR 73496, 

November 29, 2011). We are issuing this AD 

to detect and correct cracking of the fastener 

holes, which could result in rupture of the 

keel beam, and consequent reduced 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 


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(g) Retained Non-Destructive Test (NDT) 

Inspection 

This paragraph restates the requirements of 

paragraph (n) of AD 2011–24–05, 

Amendment 39–16869 (76 FR 73496, 

November 29, 2011), with new service 

information and revised credit for certain 

actions. At the applicable time in paragraph 

(g)(1) or (g)(2) of this AD, do an NDT 

inspection of the hole(s) of the horizontal 

flange of the keel beam located on frame (FR) 

40 datum on the right-hand (RH) and/or lefthand (LH) side of the fuselage, in accordance 

with the Accomplishment Instructions of the 

applicable service information specified in 

paragraph (g)(3), (g)(4), (g)(5), or (g)(6) of this 

AD. Accomplishing an inspection required 

by paragraph (j) of this AD terminates the 

inspections required by this paragraph. 

(1) For airplanes on which an inspection 

required by paragraph (h) of AD 2011–24–05, 

Amendment 39–16869 (76 FR 73496, 

November 29, 2011), has not been done as of 

January 3, 2012 (the effective date of AD 

2011–24–05): At the applicable time 

specified in paragraph (g)(1)(i) or (g)(1)(ii) of 

this AD. 

(i) For all airplanes except those identified 

in paragraph (g)(1)(ii) of this AD: Within the 

‘‘Mandatory Threshold’’ (flight cycles or 

flight hours) specified in table 1 of paragraph 

1.E.(2) of the Accomplishment Instructions of 

Airbus Service Bulletin A330–57–3081, 

including Appendix 01, Revision 04, dated 

May 31, 2011; or Airbus Service Bulletin 

A340–57–4089, including Appendix 01, 

Revision 04, dated May 31, 2011; as 

applicable; or within 3 months after January 

3, 2012 (the effective date AD 2011–24–05, 

Amendment 39–16869 (76 FR 73496, 

November 29, 2011)); whichever occurs later. 

The compliance times for configurations 02 

through 06 specified in the ‘‘Mandatory 

Threshold’’ column in table 1 of paragraph 

1.E., ‘‘Compliance,’’ are total flight cycles and 

total flight hours. 

(ii) For Model A330–201, –202, –203, –223, 

–243, –301, –321, –322, –323, –341, –342, 

and –343 airplanes, except those on which 

Airbus modification 49202 has been 

embodied in production, or Airbus Service 

Bulletin A330–57–3090 has been embodied 

in service, and Model A340–200 and –300 

series airplanes, except those on which 

Airbus modification 49202 has been 

embodied in production or Airbus Service 

Bulletin A340–57–4098 has been embodied 

in service, and except Model A340–211, 

–212, –213, –311, –312, and –313 airplanes 

on which the repair specified in Airbus 

Repair Drawing R57115053, R57115051, or 

R57115047 has been accomplished: At the 

earlier of the times specified in paragraphs 

(g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD. 

(A) Within the ‘‘Mandatory Threshold’’ 

(flight cycles or flight hours) specified in 

table 1 of paragraph 1.E.(2) of Airbus Service 

Bulletin A340–57–4089, including Appendix 

01, Revision 02, dated January 24, 2006; or 

Airbus Service Bulletin A330–57–3081, 

including Appendix 01, Revision 02, dated 

January 24, 2006; depending on the 

configuration of the aircraft model; or within 

3 months after September 13, 2007, 

whichever occurs later. The compliance 

times for Model A330 post-mod. 41652 and 

pre-mod. 44360, post-mod. 44360, and premod. 49202 (specified in Airbus Service 

Bulletin A330–57–3081, including Appendix 

01, Revision 02, dated January 24, 2006); and 

Model A340 post-mod. 41652, post-mod. 

43500 and pre-mod. 44360, post-mod. 44360 

and pre-mod. 49202, and weight variant 027 

(specified in Airbus Service Bulletin A340– 

57–4089, including Appendix 01, Revision 

02, dated January 24, 2006); specified in the 

‘‘Mandatory Threshold’’ column in table 1 of 

paragraph 1.E., ‘‘Compliance,’’ are total flight 

cycles and total flight hours. 

(B) Within the ‘‘Mandatory Threshold’’ 

(flight cycles or flight hours) specified in 

table 1 of paragraph 1.E.(2) of the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–57–3081, including 

Appendix 01, Revision 04, dated May 31, 

2011; or Airbus Service Bulletin A340–57– 

4089, including Appendix 01, Revision 04, 

dated May 31, 2011; as applicable; or within 

3 months after January 3, 2012 (the effective 

date of AD 2011–24–05, Amendment 39– 

16869 (76 FR 73496, November 29, 2011)); 

whichever occurs later. The compliance 

times for configurations 02 through 06 

specified in the ‘‘Mandatory Threshold’’ 

column in table 1 of paragraph 1.E., 

‘‘Compliance,’’ are total flight cycles and 

total flight hours. 

(2) For airplanes on which an inspection 

required by paragraph (h) of AD 2011–24–05, 

Amendment 39–16869 (76 FR 73496, 

November 29, 2011), has been done as of 

January 3, 2012 (the effective date of AD 

2011–24–05): At the earlier of the times 

specified in paragraphs (g)(2)(i) and (g)(2)(ii) 

of this AD. 

(i) Within the ‘‘Mandatory Intervals’’ given 

in table 1 of paragraph 1.E.(2) of Airbus 

Service Bulletin A340–57–4089, including 

Appendix 01, Revision 02, dated January 24, 

2006; or Airbus Service Bulletin A330–57– 

3081, including Appendix 01, Revision 02, 

dated January 24, 2006; as applicable. 

(ii) Within the applicable ‘‘Mandatory 

Interval’’ specified in table 1 of Paragraph 

1.E.(2). of Airbus Service Bulletin A330–57– 

3081, including Appendix 01, Revision 04, 

dated May 31, 2011,; or Airbus Service 

Bulletin A340–57–4089, including Appendix 

01, Revision 04, dated May 31, 2011; as 

applicable; or within 3 months after January 

3, 2012 (the effective date of AD 2011–24–05, 

Amendment 39–16869 (76 FR 73496, 

November 29, 2011)); whichever occurs later. 

(3) Airbus Service Bulletin A330–57–3081, 

including Appendix 01, Revision 04, dated 

May 31, 2011. 

(4) Airbus Service Bulletin A330–57–3081, 

including Appendix 01, Revision 05, dated 

November 13, 2012. 

(5) Airbus Service Bulletin A340–57–4089, 

including Appendix 01, Revision 04, dated 

May 31, 2011. 

(6) Airbus Service Bulletin A340–57–4089, 

Revision 05, including Appendix 01, dated 

November 13, 2012. 

(h) Retained Repetitive Inspections 

This paragraph restates the requirements of 

paragraph (p) of AD 2011–24–05, 

Amendment 39–16869 (76 FR 73496, 

November 29, 2011). If no cracking is found 

during any inspection required by paragraph 

(g) of this AD, do the actions required by 

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

(1) Before further flight: Install a new or 

oversized fastener, as applicable; seal the 

fastener; and do all other applicable actions; 

in accordance with the Accomplishment 

Instructions of the applicable service 

information specified in paragraph (g)(3), 

(g)(4), (g)(5), or (g)(6) of this AD. 

(2) Repeat the inspection required by 

paragraph (g) of this AD thereafter at 

intervals not to exceed the ‘‘Mandatory 

Intervals’’ specified in Paragraph 1.E.(2). of 

Airbus Service Bulletin A330–57–3081, 

including Appendix 01, Revision 04, dated 

May 31, 2011; or Airbus Service Bulletin 

A340–57–4089, including Appendix 01, 

Revision 04, dated May 31, 2014; as 

applicable. 

(i) Retained Corrective Action and Optional 

Modification 

(1) This paragraph restates the 

requirements of paragraph (o) of AD 2011– 

24–05, Amendment 39–16869 (76 FR 73496, 

November 29, 2011), with revised method of 

compliance language. If any cracking is 

found during any inspection required by 

paragraph (g) of this AD, 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 

Airbus’s EASA Design Organization 

Approval (DOA). 

(2) This paragraph restates the 

requirements of paragraph (r) of AD 2011– 

24–05, Amendment 39–16869 (76 FR 73496, 

November 29, 2011), with new service 

information and revised method of 

compliance language. Modifying the fastener 

installation in the junction keel beam fitting 

at FR 40, as specified in paragraph (i)(2)(i), 

(i)(2)(ii), (i)(2)(iii), or (i)(2)(iv) of this AD, as 

applicable, terminates the requirements of 

paragraphs (g) and (h) of this AD; except, for 

airplanes on which a crack was detected at 

hole 5 before oversizing of the keel beam, in 

accordance with step 3.B.(1)(b)3 of the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–57–3098, dated 

August 30, 2007; or Airbus Service Bulletin 

A340–57–4106, dated August 30, 2007; or in 

accordance with step 3.C.(2)(c) of the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–57–3098, Revision 03, 

including Appendix 01, dated September 24, 

2012, or Airbus Service Bulletin A340–57– 

4106, Revision 03, including Appendix 01, 

dated September 24, 2012; before further 

flight, repair using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. In case of any 

crack finding during any modification 

specified in this paragraph: Where the 

service information specifies to contact 

Airbus, before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA. 

(i) Modification in accordance with Airbus 

Service Bulletin A330–57–3098, dated 

August 30, 2007, before January 3, 2012 (the 

effective date of AD 2011–24–05, 


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Amendment 39–16869 (76 FR 73496, 

November 29, 2011)). 

(ii) Modification in accordance with Airbus 

Service Bulletin A330–57–3098, Revision 03, 

including Appendix 01, dated September 24, 

2012, before the effective date of this AD. 

(iii) Modification in accordance with 

Airbus Service Bulletin A340–57–4106, 

dated August 30, 2007, before January 3, 

2012 (the effective date of AD 2011–24–05, 

Amendment 39–16869 (76 FR 73496, 

November 29, 2011)). 

(iv) Modification in accordance with 

Airbus Service Bulletin A340–57–4106, 

Revision 03, including Appendix 01, dated 

September 24, 2012, before the effective date 

of this AD. 

(j) New Repetitive Rotating Probe 

Inspections 

At the applicable times specified in 

paragraphs (j)(1) and (j)(2) of this AD: Do a 

rotating probe inspection for cracking of the 

fastener hole(s) of the horizontal flange of the 

keel beam located on FR 40 datum on the RH 

and LH side of the fuselage, as applicable to 

airplane type and depending on airplane 

configuration and utilization, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A330–57–3081, 

Revision 05, including Appendix 01, dated 

November 13, 2012; or Airbus Service 

Bulletin A340–57–4089, Revision 05, 

including Appendix 01, dated November 13, 

2012; as applicable. Repeat the inspection 

thereafter at intervals not to exceed the 

‘‘Mandatory Intervals’’ specified in Paragraph 

1.E.(2)., of the Accomplishment Timescale of 

Airbus Service Bulletin A330–57–3081, 

Revision 05, including Appendix 01, dated 

November 13, 2012; or Airbus Service 

Bulletin A340–57–4089, Revision 05, 

including Appendix 01, dated November 13, 

2012; as applicable. Accomplishing an 

inspection required by this paragraph 

terminates the inspections required by 

paragraph (g) of this AD. 

(1) For airplanes on which the inspection 

required by paragraph (g) of this AD has not 

been done as of the effective date of this AD: 

Do the inspection before exceeding the 

applicable compliance times specified in the 

‘‘mandatory threshold’’ column of the tables 

in paragraph 1.E.(2)., of the Accomplishment 

Timescale of Airbus Service Bulletin A330– 

57–3081, Revision 05, including Appendix 

01, dated November 13, 2012; or Airbus 

Service Bulletin A340–57–4089, Revision 05, 

including Appendix 01, dated November 13, 

2012; as applicable; or within 12 months 

after the effective date of this AD; whichever 

occurs later. 

(2) For airplanes on which the inspection 

required by paragraph (g) of this AD has been 

done as of the effective date of this AD: Do 

the inspection within the applicable 

compliance times specified in the 

‘‘mandatory interval’’ column of the tables in 

paragraph 1.E.(2)., of the Accomplishment 

Timescale of Airbus Service Bulletin A330– 

57–3081, Revision 05, including Appendix 

01, dated November 13, 2012; or Airbus 

Service Bulletin A340–57–4089, Revision 05, 

including Appendix 01, dated November 13, 

2012; as applicable; or within 12 months 

after the effective date of this AD; whichever 

occurs later. 

(k) Credit for Previous Actions 

(1) This paragraph provides credit for the 

initial rotating probe inspection that is part 

of the inspections required by paragraphs (g) 

and (j)(1) of this AD, if those actions were 

performed before the effective date of this AD 

using the service information specified in 

paragraph (k)(1)(i) or (k)(1)(ii) of this AD. 

(i) Airbus Technical Disposition 

F57D03012810, Issue B, dated August 18, 

2003. 

(ii) Airbus Technical Disposition 582.0651/ 

2002, Issue A, dated October 17, 2002. 

(2) This paragraph restates the credit for 

the actions specified in paragraph (k) of AD 

2011–24–05, Amendment 39–16869 (76 FR 

73496, November 29, 2011), if those actions 

were performed before January 3, 2012 (the 

effective date of AD 2011–24–05), using the 

service information specified in paragraphs 

(k)(2)(i) through (k)(2)(viii) of this AD. 

(i) Airbus Service Bulletin A330–57–3081, 

dated October 30, 2003. 

(ii) Airbus Service Bulletin A330–57–3081, 

Revision 01, dated May 18, 2004. 

(iii) Airbus Service Bulletin A330–57– 

3081, Revision 02, including Appendix 01, 

dated January 24, 2006. 

(iv) Airbus Mandatory Service Bulletin 

A330–57–3081, Revision 03, dated July 31, 

2009. 

(v) Airbus Service Bulletin A340–57–4089, 

dated October 30, 2003. 

(vi) Airbus Service Bulletin A340–57– 

4089, Revision 01, dated March 2, 2004. 

(vii) Airbus Service Bulletin A340–57– 

4089, Revision 02, including Appendix 01, 

dated January 24, 2006. 

(viii) Airbus Mandatory Service Bulletin 

A340–57–4089, Revision 03, dated July 31, 

2009. 

(l) New One-Time Ultrasonic Inspection 

For airplanes in Configuration 2, as defined 

in the applicable service information 

identified in paragraph (l)(3), (l)(4), (l)(5), or 

(l)(6) of this AD, on which the modification 

has been done as of the effective date of this 

AD in accordance with the Accomplishment 

Instructions of the applicable service 

information identified in paragraph (l)(3), 

(l)(4), (l)(5), or (l)(6) of this AD; as applicable 

to airplane type; and on which fastener hole 

‘‘Nr 5’’ has been bushed before embodiment 

of Airbus Service Bulletin A330–57–3098, or 

Airbus Service Bulletin A340–57–4106, as 

applicable; or on which a crack has been 

found on fastener hole ‘‘Nr 5’’ during 

embodiment of Airbus Service Bulletin 

A330–57–3098, or Airbus Service Bulletin 

A340–57–4106, as applicable: At the 

applicable time specified in paragraph (l)(1) 

or (l)(2) of this AD, do a one-time ultrasonic 

inspection for cracking at fastener hole ‘‘Nr 

6’’ in the junction keel beam fitting at FR 40 

LH and RH sides, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–57–3117, including 

Appendix 01, dated January 25, 2013; or 

Airbus Service Bulletin A340–57–4126, 

including Appendix 01, dated January 25, 

2013; as applicable. 

(1) For Model A330–201, –202, –203, –223, 

–243, –301, –321, –322, –323, –341, –342, 

and –343 airplanes: At the later of the times 

specified in paragraphs (l)(1)(i) and (l)(1)(ii) 

of this AD. 

(i) At the applicable time specified in 

paragraph 1.E.(2)., of the Accomplishment 

Timescale of Airbus Service Bulletin A330– 

57–3117, including Appendix 01, dated 

January 25, 2013. 

(ii) Within 2,400 flight cycles or 24 months 

after the effective date of this AD, whichever 

occurs first. 

(2) For Model A340–211, –212, –213, –311, 

–312, and –313 airplanes: At the later of the 

times specified in paragraphs (l)(2)(i) and 

(l)(2)(ii) of this AD. 

(i) At the applicable time specified in 

paragraph 1.E.(2)., of the Accomplishment 

Timescale of Airbus Service Bulletin A340– 

57–4126, including Appendix 01, dated 

January 25, 2013. 

(ii) Within 1,300 flight cycles or 24 months 

after the effective date of this AD, whichever 

occurs first. 

(3) Airbus Service Bulletin A330–57–3098, 

Revision 01, dated July 31, 2009. 

(4) Airbus Service Bulletin A330–57–3098, 

Revision 02, dated June 15, 2011. 

(5) Airbus Service Bulletin A340–57–4106, 

Revision 01, dated July 31, 2009. 

(6) Airbus Service Bulletin A340–57–4106, 

Revision 02, dated June 15, 2011. 

(m) Corrective Actions 

(1) If no cracking is found during any 

inspection required by paragraph (j) of this 

AD, before further flight: Install new or 

oversized fastener, as applicable; seal the 

fastener; and do all other applicable 

corrective actions; in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–57–3081, Revision 05, 

including Appendix 01, dated November 13, 

2012; or Airbus Service Bulletin A340–57– 

4089, Revision 05, including Appendix 01, 

dated November 13, 2012; as applicable. 

Thereafter, repeat the inspection required by 

paragraph (j) of this AD at intervals not to 

exceed the ‘‘Mandatory Intervals’’ specified 

in Paragraph 1.E.(2)., of the Accomplishment 

Timescale of Airbus Service Bulletin A330– 

57–3081, Revision 05, including Appendix 

01, dated November 13, 2012; or Airbus 

Service Bulletin A340–57–4089, Revision 05, 

including Appendix 01, dated November 13, 

2012; as applicable. 

(2) If any crack is found during any 

inspection required by paragraph (j) or (l) of 

this AD; before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(n) Airplanes Excluded From Certain 

Requirements 

(1) For airplanes on which a rototest was 

done at fastener hole Nr 6 before cold 

working of the fastener hole during 

accomplishment of the actions specified in 

the applicable service information identified 

in paragraph (n)(1)(i), (n)(1)(ii), (n)(1)(iii), or 

(n)(1)(iv) of this AD: The ultrasonic 

inspection specified in paragraph (l) of this 

AD is not required. 

(i) Airbus Service Bulletin A330–57–3098, 

Revision 01, dated July 31, 2009. 

(ii) Airbus Service Bulletin A330–57–3098, 

Revision 02, dated June 15, 2011. 


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25254 Federal Register / Vol. 80, No. 85 / Monday, May 4, 2015 / Proposed Rules 

(iii) Airbus Service Bulletin A340–57– 

4106, Revision 01, dated June 31, 2009. 

(iv) Airbus Service Bulletin A340–57– 

4106, Revision 02, dated June 15, 2011. 

(2) For airplanes that have been modified 

as of the effective date of this AD in 

accordance with the Accomplishment 

Instructions of the applicable service 

information identified in paragraph (n)(1)(i), 

(n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of this AD: 

No action is required by this paragraph, 

except as otherwise required by paragraph (l) 

of this AD and, provided that if any crack 

was found during any modification specified 

in this paragraph and the service information 

specified to contact Airbus, repair was done 

before further flight using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(o) Optional Terminating Actions 

(1) Modification of an airplane in 

accordance with the Accomplishment 

Instructions of the applicable service 

information identified in paragraph (o)(1)(i), 

(o)(1)(ii), (o)(1)(iii), (o)(1)(iv), (o)(1)(v), or 

(o)(1)(vi) of this AD; as applicable to airplane 

type and depending on airplane 

configuration; terminates the requirements of 

this AD, provided that in case of any crack 

finding during any modification specified in 

this paragraph, and the service information 

specifies to contact Airbus, repair is done 

before further flight, using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or EASA; or Airbus’s EASA 

DOA. If approved by the DOA, the approval 

must include the DOA-authorized signature 

(i) Airbus Service Bulletin A330–57–3090, 

dated March 27, 2006. 

(ii) Airbus Service Bulletin A330–57–3090, 

Revision 01, dated June 15, 2011. 

(iii) Airbus Service Bulletin A330–57– 

3098, Revision 03, including Appendix 01, 

dated September 24, 2012. 

(iv) Airbus Service Bulletin A340–57– 

4098, dated March 27, 2006. 

(v) Airbus Service Bulletin A340–57–4098, 

Revision 01, dated June 15, 2011. 

(vi) Airbus Service Bulletin A340–57– 

4106, Revision 03, including Appendix 01, 

dated September 24, 2012. 

(2) Accomplishment of the ultrasonic 

inspection required by paragraph (l) of this 

AD and all applicable corrective actions 

required by paragraph (m) of this AD 

terminates the requirements of this AD for 

those airplanes. 

(p) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; 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) AMOCs approved previously for AD 

2011–24–05, Amendment 39–16869 (76 FR 

73496, November 29, 2011), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(3) 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, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0010R1, dated 

May 5, 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– 

2015–0937. 

(2) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@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 April 13, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–10177 Filed 5–1–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0934; Directorate 

Identifier 2014–NM–030–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 all 

Dassault Aviation Model FAN JET 

FALCON, FAN JET FALCON SERIES C, 

D, E, F, and G airplanes; Model 

MYSTERE–FALCON 200 airplanes; and 

Model MYSTERE–FALCON 20–C5, 20– 

D5, 20–E5, and 20–F5 airplanes. This 

proposed AD was prompted by reports 

of defective fire extinguisher tubes. It 

was determined the defects were caused 

by corrosion. This proposed AD would 

require repetitive general visual 

inspections of the fire extinguisher 

tubes for cracking and corrosion, and 

replacement of any cracked tube with a 

serviceable tube, if necessary. We are 

proposing this AD to detect and correct 

cracking and corrosion in the fire 

extinguisher tubes, which could impact 

the capability to extinguish an engine 

fire, and possibly result in damage to 

the airplane and injury to the 

passengers. 

DATES: We must receive comments on 

this proposed AD by June 18, 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. 

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– 

0934; 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, 


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