This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

36666 

Vol. 79, No. 125 

Monday, June 30, 2014 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0425; Directorate 

Identifier 2013–NM–180–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) 2012–06– 

19, 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 2012–06– 

19 currently requires repetitive 

inspections of the main fitting and 

sliding tube of the nose landing gear 

(NLG) for defects, damage, and cracks; 

and corrective actions if necessary. 

Since we issued AD 2012–06–19, we 

have determined that additional 

airplanes are affected by the identified 

unsafe condition. This proposed AD 

would add airplanes to the 

applicability. This proposed AD would 

require an inspection of the part number 

and serial number of the NLG main 

fitting and NLG sliding tube; for affected 

parts, a magnetic particle inspection 

(MPI) for cracks, and flap peening and 

replacement if necessary. This proposed 

AD would also require, for certain parts, 

additional inspections for damage and 

cracking. We are proposing this AD to 

detect and correct cracks, defects, or 

damage of the main fitting or sliding 

tube, which could result in consequent 

NLG collapse. 

DATES: We must receive comments on 

this proposed AD by August 14, 2014. 

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://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0425; or in person at the Docket 

Operations office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

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–2014–0425; Directorate Identifier 

2013–NM–180–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 March 15, 2012, we issued AD 

2012–06–19, Amendment 39–17000 (77 

FR 22188, April 13, 2012). AD 2012–06– 

19 requires actions intended to address 

an unsafe condition on 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. 

Since we issued AD 2012–06–19, 

Amendment 39–17000 (77 FR 22188, 

April 13, 2012), we have determined 

that additional airplanes are affected by 

the identified unsafe condition. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0179, 

dated August 7, 2013 (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 the overhaul of two different Nose 

Landing Gear (NLG) units, cracks were found 

on the main fitting of one and the sliding 

tube of the other. Investigations concluded 

that the cracks initiated as a result of residual 

stress in the parts, following damage due to 

impact during towing incidents. 

A subsequent review of the reported 

incidents identified a specific group of NLG 

main fittings and sliding tubes that may have 

sustained impact damage as a result of 

towing incidents. 

This condition, if not detected and 

corrected could lead to NLG collapse. 


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To address this potential unsafe condition, 

EASA issued AD 2010–0034 [(http://

ad.easa.europa.eu/blob/easa_ad_2010_0034_

Corrected_superseded.pdf/AD_2010-0034_1) 

[which corresponds to FAA AD 2012–06–19, 

Amendment 39–17000 (77 FR 22188, April 

13, 2012)] to require accomplishment of a 

one-time Magnetic Particles Inspection (MPI), 

followed by repetitive Detailed Visual 

Inspections (DVI) of the main fittings and 

sliding tubes of the affected NLG units 

identified by Part Number (P/N) and Serial 

Number (S/N) in the Applicability section of 

that AD and, depending on findings, 

accomplishment of applicable corrective 

actions. 

Since that [EASA] AD was issued, it has 

been found necessary to address the issue at 

the level of NLG detail parts and no longer 

at NLG assembly level, as some detail parts 

have been transferred from an aeroplane to 

another. Airbus revised the applicable 

Service Bulletins (SB), which now list the 

affected NLG main fittings and sliding tubes. 

For the reasons described above, this 

[EASA] AD retains [certain] requirements of 

EASA AD 2010–0034 which is superseded 

and requires [an inspection of the part 

number and serial number of the NLG main 

fitting and NLG sliding tube, and for affected 

parts,] a one-time MPI [for cracks], followed 

by repetitive DVI [for cracking, damage to 

paint, sealant, cadmium, and base metal] of 

the affected NLG main fittings and sliding 

tubes and, depending on inspection results, 

accomplishment of corrective actions [e.g., 

flap peening and replacing cracked parts]. 

This AD also extends the applicability to 

A330 freighters. 

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– 

0425. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A330–32–3233, Revision 02, dated 

January 27, 2014; and Service Bulletin 

A340–32–4275, Revision 01, dated July 

5, 2013. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

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 92 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

The actions that are required by AD 

2012–06–19, Amendment 39–17000 (77 

FR 22188, April 13, 2012), and retained 

in this proposed AD take about 4 workhours per product, at an average labor 

rate of $85 per work-hour. Required 

parts cost about $0 per product. Based 

on these figures, the estimated cost of 

the actions that are required by AD 

2012–06–19 is $31,280 per product. 

We also estimate that it would take 

about 10 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 $0 per product. 

Based on these figures, we estimate the 

cost of this proposed AD on U.S. 

operators to be $78,200, or $850 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 114 work-hours and require parts 

costing $435,000, for a cost of $444,690 

per product. We have no way of 

determining the number of aircraft that 

might need these actions. 

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 proposed 

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) 

2012–06–19, Amendment 39–17000 (77 

FR 22188, April 13, 2012), and adding 

the following new AD: 

Airbus: Docket No. FAA–2014–0425; 

Directorate Identifier 2013–NM–180–AD. 

(a) Comments Due Date 

We must receive comments by August 14, 

2014. 

(b) Affected ADs 

This AD supersedes AD 2012–06–19, 

Amendment 39–17000 (77 FR 22188, April 

13, 2012). 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –223, –223F –243, –243F, 

–301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model A340– 

211, –212, –213, –311, –312, and –313 

airplanes; certificated in any category; all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by reports of a 

cracked nose landing gear (NLG) main fitting 

and sliding tube during overhaul of the NLGs 

following damage due to impact during 

towing incidents. We are issuing this AD to 

detect and correct cracks, defects, or damage 

of the main fitting or sliding tube, which 

could result in consequent NLG collapse. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
36668 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Proposed Rules 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Detailed Inspection and 

Corrective Actions 

This paragraph restates the requirements of 

paragraph (g) of AD 2012–06–19, 

Amendment 39–17000 (77 FR 22188, April 

13, 2012) with revised service information. 

For Model A330–201, –202, –203, –223, 

–243, –301, –302, –303, –321, –322, –323, 

–341, –342, and –343 airplanes; and Model 

A340–211, –212, –213, –311, –312, and –313 

airplanes; if fitted with the NLG identified in 

table 1 to paragraph (g) of this AD: Within 

900 flight hours after April 30, 2012 (the 

effective date of AD 2012–06–19), do a 

detailed inspection of the NLG main fitting 

and sliding tube for any cracks, defects, and 

damage of the paint or surface protection, 

including paint removal and cracking of the 

surface treatment. Before further flight after 

doing the detailed inspection of the NLG, 

remove the labels, paint, surface protection 

coatings, and cadmium from the NLG main 

fitting; do a detailed inspection for any 

damage to the surface that will impair the 

magnetic particle inspection (MPI); and, if 

any defects are found, before further flight, 

remove any defects by polishing. Do all 

actions specified in paragraph (g) of this AD 

in accordance with the Accomplishment 

Instructions of the applicable service 

information specified in paragraph (g)(1) or 

(g)(2) of this AD. 

(1) For Model A330 airplanes: Airbus 

Mandatory Service Bulletin A330–32–3233, 

dated October 22, 2009; or Airbus Service 

Bulletin A330–32–3233, Revision 02, dated 

January 27, 2014. 

(2) For Model A340 airplanes: Airbus 

Mandatory Service Bulletin A340–32–4275, 

dated October 22, 2009; or Airbus Service 

Bulletin A340–32–4275, Revision 01, dated 

July 5, 2013. 

TABLE 1 TO PARAGRAPH (g) OF THIS

AD—APPLICABLE NLG AND SERIAL

NUMBERS

Part No. Serial No. 

D23285200 ................................. B2 

D23285101–7 ............................. B58 

D23285101–10 ........................... B75 

D23581100–1 ............................. B124 

D23581100–1 ............................. B159 

D23581100–7 ............................. B386 

D23581100–7 ............................. B398 

D23581100–7 ............................. B400 

D23581100–7 ............................. B403 

(h) Retained Magnetic Particle Inspection 

This paragraph restates the requirements of 

paragraph (h) of AD 2012–06–19, 

Amendment 39–17000 (77 FR 22188, April 

13, 2012), with revised service information. 

Before further flight after doing the actions 

required in paragraph (g) of this AD: Do an 

MPI for cracking of the NLG main fitting and 

sliding tube, in accordance with the 

Accomplishment Instructions of the 

applicable service information specified in 

paragraph (g)(1) or (g)(2) of this AD. 

(1) If no crack is detected during the MPI 

required by paragraph (h) of this AD: Before 

further flight, flap peen the inspected area 

where the paint and cadmium has been 

removed, and replace the protective coatings, 

in accordance with the Accomplishment 

Instructions of the applicable service 

information specified in paragraph (g)(1) or 

(g)(2) of this AD. 

(2) If any crack is detected during the MPI 

required by paragraph (h) of this AD: Before 

further flight, replace the damaged part with 

a new or serviceable part, in accordance with 

the Accomplishment Instructions of the 

applicable service information specified in 

paragraph (g)(1) or (g)(2) of this AD. 

(i) New Requirement of This AD: 

Identification 

Within 1,000 flight hours after the effective 

date of this AD, identify the part number and 

serial number of the NLG main fitting and 

NLG sliding tube, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3233, Revision 02, 

dated January 27, 2014; or Airbus Service 

Bulletin A340–32–4275, Revision 01, dated 

July 5, 2013; as applicable. A review of 

airplane maintenance records is acceptable in 

lieu of this identification if the part number 

and the serial number of the NLG main fitting 

and NLG sliding tube can be conclusively 

determined from that review. 

(j) New Requirement of This AD: MPI 

If, during the identification required by 

paragraph (i) of this AD, it is determined any 

NLG main fitting or NLG sliding tube is 

installed and the fitting or tube has a part 

number and serial number listed in Airbus 

Service Bulletin A330–32–3233, Revision 02, 

dated January 27, 2014; or Airbus Service 

Bulletin A340–32–4275, Revision 01, dated 

July 5, 2013; as applicable: Within 1,000 

flight hours after the effective date of this AD, 

do an MPI for cracks of the affected parts, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

32–3233, Revision 02, dated January 27, 

2014; or Airbus Service Bulletin A340–32– 

4275, Revision 01, dated July 5, 2013; as 

applicable. Accomplishing the MPI required 

by this paragraph terminates the inspections 

required by paragraphs (g) and (h) of this AD. 

(1) If any crack is detected during the MPI 

required by paragraph (j) of this AD, before 

further flight, replace any cracked part (NLG 

main fitting and NLG sliding tube) with a 

serviceable one, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3233, Revision 02, 

dated January 27, 2014; or Airbus Service 

Bulletin A340–32–4275, Revision 01, dated 

July 5, 2013; as applicable. 

(2) If no crack is detected during the MPI 

required by paragraph (j) of this AD, before 

further flight, do a flap peening to introduce 

compressive residual stress and corrosion 

protection, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3233, Revision 02, 

dated January 27, 2014; or Airbus Service 

Bulletin A340–32–4275, Revision 01, dated 

July 5, 2013; as applicable. 

(k) New Requirement of This AD: Detailed 

Inspection 

Within 900 flight hours after doing the flap 

peening required by paragraph (j)(2) of this 

AD, do a detailed inspection for damage to 

paint, damage to the sealant around the 

labels, damage to the cadmium or base metal, 

and for cracking of the affected parts; in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

32–3233, Revision 02, dated January 27, 

2014; or Airbus Service Bulletin A340–32– 

4275, Revision 01, dated July 5, 2013; as 

applicable. Repeat the inspection thereafter 

at intervals not to exceed 900 flight hours. 

(1) If damage to the paint, damage to the 

sealant around the labels, or damage to the 

cadmium or base metal, is detected during 

any detailed inspection required by 

paragraph (k) of this AD, before further flight, 

do an MPI for cracking of the affected parts, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

32–3233, Revision 02, dated January 27, 

2014; or Airbus Service Bulletin A340–32– 

4275, Revision 01, dated July 5, 2013; as 

applicable. 

(2) If any cracking is detected during any 

inspection required by paragraph (k) or (k)(1) 

of this AD, before further flight, replace any 

cracked part with a serviceable part, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

32–3233, Revision 02, dated January 27, 

2014; or Airbus Service Bulletin A340–32– 

4275, Revision 01, dated July 5, 2013; as 

applicable. 

(l) Terminating Action 

Replacement of a part as required by 

paragraph (j)(1) or (k)(2) of this AD is 

terminating action for the repetitive detailed 

inspections required by paragraph (k) of this 

AD for that part, provided that the part 

number and serial number of the replacement 

part is not listed in Airbus Service Bulletin 

A330–32–3233, Revision 02, dated January 

27, 2014; or Airbus Service Bulletin A340– 

32–4275, Revision 01, dated July 5, 2013; as 

applicable. 

(m) Parts Installation Limitation 

As of the effective date of this AD, 

installation of an NLG main fitting or NLG 

sliding tube having a part number and serial 

number listed in Airbus Service Bulletin 

A330–32–3233, Revision 02, dated January 

27, 2014; or Airbus Service Bulletin A340– 

32–4275, Revision 01, dated July 5, 2013; as 

applicable; is allowed, provided that the NLG 

main fitting and NLG sliding tube has not 

accumulated more than 900 flight hours 

since the most recent inspection 

accomplished in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3233, Revision 02, 

dated January 27, 2014; or Airbus Service 

Bulletin A340–32–4275, Revision 01, dated 

July 5, 2013; as applicable. 

(n) Credit for Previous Actions 

This paragraph provides credit for 

inspections required by paragraphs (j) and (k) 

of this AD and the flap peening required by 

paragraph (j)(2) of this AD, if those actions 

were performed before the effective date of 


emcdonald on DSK67QTVN1PROD with PROPOSALS
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this AD using the service information 

specified in paragraph (n)(1), (n)(2), or (n)(3) 

of this AD. 

(1) Airbus Service Bulletin A330–32–3233, 

dated October 22, 2009. 

(2) Airbus Service Bulletin A330–32–3233, 

Revision 01, dated July 5, 2013. 

(3) Airbus Service Bulletin A340–32–4275, 

dated October 22, 2009. 

(o) 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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or by the Design 

Approval Holder with a State of Design 

Authority’s design organization approval, as 

applicable). You are required to ensure the 

product is airworthy before it is returned to 

service. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0179, dated August 7, 2013, 

for related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2014–0425. 

(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 June 19, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–15254 Filed 6–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0423; Directorate 

Identifier 2013–NM–233–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 DC–10–10, 

DC–10–10F, DC–10–30, DC–10–30F 

(KC–10A and KDC–10), DC–10–40, MD– 

10–10F, and MD–10–30F airplanes. This 

proposed AD was prompted by an 

evaluation by the design approval 

holder (DAH) indicating that the 

forward cargo compartment frames are 

subject to widespread fatigue damage 

(WFD). This proposed AD would 

require an inspection of the attachment 

holes at the forward cargo compartment 

frames and the cargo liner for cracking, 

and repair if necessary. This proposed 

AD would also require installing new 

oversized fasteners in the forward cargo 

compartment frames. We are proposing 

this AD to prevent fatigue cracking of 

the forward cargo compartment frames, 

which could result in loss of the failsafe structural integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by August 14, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, CA 90846–0001; telephone 

206–544–5000, extension 2; fax 206– 

766–5683; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA 98057–3356. 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– 

0423; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Nenita Odesa, Aerospace Engineer, 

Airframe Branch, ANM–120L, Los 

Angeles Aircraft Certification Office 

(ACO), FAA, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5234; fax: 562–627– 

5210; email: nenita.odesa@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2014–0423; Directorate Identifier 2013– 

NM–233–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 because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 


emcdonald on DSK67QTVN1PROD with PROPOSALS