Federal Register / Vol. 80, No. 223 / Thursday, November 19, 2015 / Proposed Rules 72395 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2015–5808; Directorate Identifier 2015– 

NM–111–AD. 

(a) Comments Due Date 

We must receive comments by January 4, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 787–8 series airplanes, certificated in 

any category, as identified in the service 

information specified in paragraphs (c)(1), 

(c)(2), and (c)(3) of this AD. 

(1) Boeing Alert Service Bulletin B787– 

81205–SB380009–00, Issue 001, dated March 

26, 2015. 

(2) Boeing Alert Service Bulletin B787– 

81205–SB530029–00, Issue 001, dated March 

26, 2015. 

(3) Boeing Alert Service Bulletin B787– 

81205–SB530031–00, Issue 001, dated March 

26, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 38, Water/Waste; and Code 53, 

Fuselage. 

(e) Unsafe Condition 

This proposed AD was prompted by 

reports of water leakage from the potable 

water system due to improperly installed 

waterline couplings, and water leaking into 

the electronics equipment (EE) bays from 

above the floor in the main cabin, resulting 

in water on the equipment in the EE bays. We 

are issuing this AD to prevent a water leak 

from an improperly installed potable water 

system coupling, or main cabin water source, 

which could cause the equipment in the EE 

bays to become wet, resulting in an electrical 

short and potential loss of system functions 

essential for safe flight. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replace Potable Waterline Couplings 

Within 24 months after the effective date 

of this AD: Replace the existing potable 

waterline couplings located above the 

forward and aft EE bays with new, improved 

couplings, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin B787–81205–SB380009–00, 

Issue 001, dated March 26, 2015. Before 

further flight after doing the replacement, do 

a potable water system leak test and repair 

any leaks found before further flight, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

B787–81205–SB380009–00, Issue 001, dated 

March 26, 2015. 

(h) Seal Floor Panels and Seat Tracks/Install 

Drip Shields and Reroute Wiring 

Within 60 months after the effective date 

of this AD: Do the actions specified in 

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

(1) Apply sealant to the main cabin floor 

areas located above the aft EE bay, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

B787–81205–SB530029–00, Issue 001, dated 

March 26, 2015. 

(2) Install drip shields and foam blocks, 

and reroute the wire bundles above the 

equipment in the aft EE bay, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin B787–81205– 

SB530031–00, Issue 001, dated March 26, 

2015. 

(i) 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 (j)(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, 

alteration, or modification required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair method, 

modification deviation, or alteration 

deviation must meet the certification basis of 

the airplane, and the approval must 

specifically refer to this AD. 

(4) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

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

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(j) Related Information 

(1) For more information about this AD, 

contact Susan L. Monroe, Aerospace 

Engineer, Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6457; fax: 425–917–6590; 

email: susan.l.monroe@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. You 

may view this referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on 

November 9, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–29441 Filed 11–18–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4817; Directorate 

Identifier 2014–NM–115–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) 95–18–08, 

for all Airbus Model A300–600 series 

airplanes. AD 95–18–08 currently 

requires repetitive inspections to detect 

cracks in the bottom skin of the wing in 

the area of the cut out for the pylon rear 

attachment fitting, and repair if 

necessary. Since we issued AD 95–18– 

08, we received a report that updated 

fatigue and damage tolerance analyses 

and a fleet survey found that certain 

inspection thresholds and intervals 

must be reduced to allow more timely 

findings of cracking. This proposed AD 

would, for certain airplanes, reduce the 

compliance times for the inspections. 

We are proposing this AD to detect and 

correct such fatigue-related cracking, 

which could result in reduced structural 

integrity of the wing. 

DATES: We must receive comments on 

this proposed AD by January 4, 2016. 

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. 


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• 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—EAW, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

4817; 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

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–2015–4817; Directorate Identifier 

2014–NM–115–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 August 29, 1995, we issued AD 

95–18–08, Amendment 39–9355 (60 FR 

47677, September 14, 1995). AD 95–18– 

08 requires actions intended to address 

an unsafe condition on all Airbus Model 

A300–600 series airplanes (which 

includes Airbus Model A300 C4–605R 

Variant F airplanes, Model A300 B4– 

622 airplanes, and Model A300 F4– 

622R airplanes that were added to the 

U.S. Type Certificate Data Sheet since 

issuance of AD 95–18–08). 

Since we issued AD 95–18–08, 

Amendment 39–9355 (60 FR 47677, 

September 14, 1995), we received a 

report that updated fatigue and damage 

tolerance analyses and a fleet survey 

done to support a second extended 

service goal for Model A300–600 series 

airplanes found that certain inspection 

thresholds and intervals must be 

reduced to allow more timely findings 

of cracking. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0119, dated May 13, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on all Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

series airplanes, and Model A300 C4– 

605R Variant F airplanes (collectively 

called Model A300–600 series 

airplanes). The MCAI states: 

Full-scale fatigue tests carried out on the 

A300–600 test specimen by Airbus revealed 

crack initiation in the bottom skin adjacent 

to the aft pylon attachment fitting. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To address this unsafe condition, DGAC 

[Direction Ge ́ne ́rale de l’Aviation Civile] 

France issued AD 94–069–158(B) (http://

ad.easa.europa.eu/blob/1994069158tb_

superseded.pdf/AD_F-1994-069-158_2) 

[which corresponds to FAA AD 95–18–08, 

Amendment 39–9355 (60 FR 47677, 

September 14, 1995)] to require repetitive 

detailed visual inspections (DVI) of the wing 

bottom skin in the area of the cut-out for the 

pylon rear attachment fitting on Left Hand 

(LH) and Right Hand (RH) wings [to detect 

cracks, and repair if necessary]. 

Since that [DGAC] AD was issued, a fleet 

survey and updated Fatigue and Damage 

Tolerance analyses have been performed in 

order to substantiate the second A300–600 

Extended Service Goal (ESG2) exercise. As a 

result, it was revealed that the inspection 

threshold and interval must be reduced to 

allow timely detection of cracks and the 

accomplishment of an applicable corrective 

action. Prompted by these findings, Airbus 

issued Revision 07 of Service Bulletin (SB) 

A300–57–6028. 

For the reasons described above, this 

[EASA] AD retains the requirements of DGAC 

France AD 94–069–158(B), which is 

superseded, but reduces the inspection 

thresholds and intervals [e.g., compliance 

times]. 

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– 

4817. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Airbus Service Bulletin 

A300–57–6028, Revision 07, dated June 

6, 2011. The service information 

describes procedures for inspections to 

detect cracks in the bottom skin of the 

wing in the area of the cut out for the 

pylon rear attachment fitting, and 

repair. This service information is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section of this NPRM. 

FAA’s Determination 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 124 airplanes of U.S. registry. 

The actions that are required by AD 

95–18–08, Amendment 39–9355 (60 FR 

47677, September 14, 1995), and 

retained in this proposed AD take about 

6 work-hours per product, at an average 

labor rate of $85 per work-hour. Based 

on these figures, the estimated cost of 

the actions that are required by AD 95– 

18–08 is $510 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 15 work-hours and require parts 

costing $10,000, for a cost of $11,275 

per product. We have no way of 


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determining the number of aircraft that 

might need these actions. 

The new requirements of this 

proposed AD add no additional 

economic burden. 

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) 

95–18–08, Amendment 39–9355 (60 FR 

47677, September 14, 1995), and adding 

the following new AD: 

Airbus: Docket No. FAA–2015–4817; 

Directorate Identifier 2014–NM–115–AD. 

(a) Comments Due Date 

We must receive comments by January 4, 

2016. 

(b) Affected ADs 

This AD replaces AD 95–18–08, 

Amendment 39–9355 (60 FR 47677, 

September 14, 1995). 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) through (c)(4) of this AD, 

certificated in any category, all manufacturer 

serial numbers. 

(1) Airbus Model A300 B4–601, B4–603, 

B4–620, and B4–622 airplanes. 

(2) Airbus Model A300 B4–605R and B4– 

622R airplanes. 

(3) Airbus Model A300 F4–605R and F4– 

622R airplanes. 

(4) Airbus Model A300 C4–605R Variant F 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a report that 

updated fatigue and damage tolerance 

analyses and a fleet survey found that certain 

inspection thresholds and intervals must be 

reduced to allow more timely findings of 

cracking. We are issuing this AD to detect 

and correct such fatigue-related cracking, 

which could result in reduced structural 

integrity of the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection and Corrective 

Action With Additional Repair Information 

This paragraph restates the requirements of 

paragraph (a) of AD 95–18–08, Amendment 

39–9355 (60 FR 47677, September 14, 1995), 

with additional repair contact information. 

Prior to the accumulation of 24,000 total 

flight cycles since date of manufacture of the 

airplane, or within 750 flight cycles after 

October 16, 1995 (the effective date of AD 

95–18–08), whichever occurs later, perform a 

detailed visual inspection to detect cracks in 

the bottom skin of the wing in the area of the 

cut out for the pylon rear attachment fitting, 

in accordance with Airbus Service Bulletin 

A300–57–6028, Revision 3, dated September 

13, 1994. Repeat the inspection thereafter at 

intervals not to exceed 9,000 flight cycles. If 

any crack is detected, prior to further flight, 

repair the wing bottom skin in accordance 

with a method approved by the Manager, 

Standardization Branch, ANM–113, FAA, 

Transport Airplane Directorate, or 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). Accomplishing any 

inspection required by paragraph (h) of this 

AD terminates the inspections required by 

this paragraph. 

(h) New Requirement of This AD: Revised 

Inspection Thresholds and Intervals 

Within the applicable compliance times 

required in paragraphs (h)(1) and (h)(2) of 

this AD, do a detailed visual inspection of 

the wing bottom skin in the area of the cutout for the pylon rear attachment fitting on 

left-hand and right-hand wings, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–6028, Revision 07, dated June 6, 2011. 

Repeat the inspections thereafter at the 

applicable intervals required in paragraphs 

(h)(3) and (h)(4) of this AD. Accomplishing 

any inspection required by this paragraph 

terminates the inspections required by 

paragraph (g) of this AD. 

(1) For ‘‘normal range operations’’ 

airplanes having an average flight time of 1.5 

flight hours or more: Do the inspection at the 

applicable time required in paragraphs 

(h)(1)(i) and (h)(1)(ii) of this AD. 

(i) For Model A300 F4–605R and F4–622R 

airplanes: Do the inspection at the later of the 

times specified in paragraphs (h)(1)(i)(A) and 

(h)(1)(i)(B) of this AD. 

(A) Within 24,000 flight cycles or 51,800 

flight hours after first flight of the airplane, 

whichever occurs first. 

(B) Within 2,000 flight cycles or 4,300 

flight hours after the effective date of this AD, 

whichever occurs first. 

(ii) For Model A300 B4–600, B4–600R, and 

Model A300 C4–605R Variant F airplanes: Do 

the inspection at the later of the times 

specified in paragraphs (h)(1)(ii)(A) and 

(h)(1)(ii)(B) of this AD. 

(A) Within 19,100 flight cycles or 41,200 

flight hours after first flight of the airplane, 

whichever occurs first. 

(B) Within 1,500 flight cycles or 3,200 

flight hours after the effective date of this AD, 

whichever occurs first. 

(2) For ‘‘short range operations’’ airplanes 

having an average flight time of less than 1.5 

flight hours: Do the inspection at the 

applicable time required in paragraphs 

(h)(2)(i) and (h)(2)(ii) of this AD. 

(i) For Model A300 F4–605R and F4–622R 

airplanes: Do the inspection at the later of the 

times specified in paragraphs (h)(2)(i)(A) and 

(h)(2)(i)(B) of this AD. 

(A) Within 25,900 flight cycles or 38,800 

flight hours after first flight of the airplane, 

whichever occurs first. 

(B) Within 2,100 flight cycles or 3,200 

flight hours after the effective date of this AD, 

whichever occurs first. 

(ii) For Model A300 B4–600, B4–600R, and 

Model A300 C4–605R Variant F airplanes: Do 


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the inspection at the later of the times 

specified in paragraphs (h)(2)(ii)(A) and 

(h)(2)(ii)(B) of this AD. 

(A) Within 20,600 flight cycles or 30,900 

flight hours after first flight of the airplane, 

whichever occurs first. 

(B) Within 1,600 flight cycles or 2,400 

flight hours after the effective date of this AD, 

whichever occurs first. 

(3) For ‘‘normal range operations’’ 

airplanes having an average flight time of 1.5 

flight hours or more: Repeat the inspection at 

the applicable time required in paragraphs 

(h)(3)(i) and (h)(3)(ii) of this AD. 

(i) For Model A300 F4–605R and F4–622R 

airplanes: Repeat the inspection thereafter at 

intervals not to exceed 9,000 flight cycles or 

19,400 flight hours, whichever occurs first. 

(ii) For Model A300 B4–600, B4–600R, and 

Model A300 C4–605R Variant F airplanes: 

Repeat the inspection thereafter at intervals 

not to exceed 7,100 flight cycles or 15,300 

flight hours, whichever occurs first. 

(4) For ‘‘short range operations’’ airplanes 

having an average flight time of less than 1.5 

flight hours: Repeat the inspection at the 

applicable time required in paragraphs 

(h)(4)(i) and (h)(4)(ii) of this AD. 

(i) For Model A300 F4–605R and F4–622R 

airplanes: Repeat the inspection thereafter at 

intervals not to exceed 9,700 flight cycles or 

14,500 flight hours, whichever occurs first. 

(ii) For Model A300 B4–600, B4–600R, and 

Model A300 C4–605R Variant F airplanes: 

Repeat the inspection thereafter at intervals 

not to exceed 7,600 flight cycles or 11,500 

flight hours, whichever occurs first. 

(i) Definition of Average Flight Time for 

Paragraph (h) of This AD 

For the purpose of paragraph (h) of this 

AD, the Average Flight Time must be 

established as follows: 

(1) For the initial inspection, the average 

flight time is the total accumulated flight 

hours, counted from take-off to touch-down, 

divided by the total accumulated flight cycles 

at the effective date of this AD. 

(2) For the first repeated inspection 

interval, the average flight time is the total 

accumulated flight hours divided by the total 

accumulated flight cycles at the time of the 

inspection threshold. 

(3) For all inspection intervals onwards, 

the average flight time is the flight hours 

divided by the flight cycles accumulated 

between the last two inspections. 

(j) New Requirement of This AD: Corrective 

Action for Any Cracking Found 

If any crack is found during any inspection 

required by paragraph (h) 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. Accomplishing a repair does not 

constitute terminating action for the 

repetitive inspections required by paragraph 

(h) of this AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for 

inspections required by paragraph (h) of this 

AD, if those actions were performed before 

the effective date of this AD using any of the 

service information identified in paragraphs 

(k)(1), (k)(2), and (k)(3) of this AD, which are 

not incorporated by reference in this AD. 

(1) Airbus Service Bulletin A300–57–6028, 

Revision 04, dated October 25, 1999. 

(2) Airbus Service Bulletin A300–57–6028, 

Revision 05, dated January 11, 2002. 

(3) Airbus Service Bulletin A300–57–6028, 

Revision 06, dated May 17, 2006. 

(l) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 

(i) 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. 

(ii) AMOCs approved previously for AD 

95–18–08, Amendment 39–9355 (60 FR 

47677, September 14, 1995), are approved as 

AMOCs for the corresponding provisions of 

paragraph (g) of this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2014–0119, dated May 13, 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–2015–4817. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

You may view this service information at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on 

November 11, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–29443 Filed 11–18–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4815; Directorate 

Identifier 2015–NM–112–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) 2015–03– 

06, for all Airbus Model A330–200, 

A330–200 Freighter, A330–300, A340– 

200, A340–300, A340–500, and A340– 

600 series airplanes. AD 2015–03–06 

currently requires repetitive inspections 

of the left-hand and right-hand wing 

main landing gear (MLG) rib 6 aft 

bearing lugs (forward and aft) to detect 

any cracks on the two lugs, and 

replacement if necessary. Since we 

issued AD 2015–03–06, we have 

received reports of additional cracking 

of the MLG rib 6 aft bearing lugs. This 

proposed AD would reduce certain 

compliance times. We are proposing 

this AD to detect and correct cracking of 

the MLG rib 6 aft bearing lugs, which 

could result in collapse of the MLG 

upon landing. 

DATES: We must receive comments on 

this proposed AD by January 4, 2016. 

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, 


rmajette on DSK2TPTVN1PROD with PROPOSALS