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

61327 

Vol. 80, No. 197 

Tuesday, October 13, 2015 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3985; Directorate 

Identifier 2014–NM–182–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) 2010–04– 

03, for all Airbus Model A310 series 

airplanes. AD 2010–04–03 currently 

requires accomplishing repetitive 

detailed visual inspections for cracking 

around the fastener holes in certain 

wing top skin panels between the right 

side and left side of the front and rear 

spars, and repair if needed. Since we 

issued AD 2010–04–03, Airbus 

improved the ultrasonic inspection 

program to allow earlier crack detection 

and to extend the repetitive inspection 

intervals. We have determined these 

inspections are necessary to address the 

unsafe condition. This proposed AD 

would continue to require the repetitive 

detailed inspections for cracking around 

the fastener holes in certain wing top 

skin panels between the front and rear 

spars, and repair if needed, and would 

require supplemental repetitive 

ultrasonic inspections for cracking 

around the fastener holes in certain 

wing top skin panels and repair if 

needed. We are proposing this AD to 

detect and correct cracking around the 

fastener holes in certain wing top skin 

panels between the right side and left 

side of the front and rear spars, which 

could result in reduced structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by November 27, 

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—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– 

3985; 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–2015–3985; Directorate Identifier 

2014–NM–182–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 January 28, 2010, we issued AD 

2010–04–03, Amendment 39–16196 (75 

FR 6852, February 12, 2010). AD 2010– 

04–03 requires actions intended to 

address an unsafe condition on all 

Airbus Model A310 series airplanes. 

Since we issued AD 2010–04–03, 

Amendment 39–16196 (75 FR 6852, 

February 12, 2010), the manufacturer 

improved the ultrasonic inspection 

program to allow earlier crack detection 

and to extend the repetitive inspection 

intervals. We have determined these 

inspections are necessary to address the 

unsafe condition. 

The European Aviation Safety 

Agency, which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2014–0200R1, 

dated September 19, 2014 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

on all Airbus Model A310 series 

airplanes. The MCAI states: 

Following scheduled maintenance, cracks 

were found around the wing top skin panels 

fastener holes at Rib 2, between Stringer 

(STG) 2 and STG14. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. The General Visual 

Inspection required by the existing 

applicable Airworthiness Limitation Items 

(ALI) tasks may not be adequate to detect 

these cracks. 

To address this issue, Airbus developed an 

inspection programme based on repetitive 

detailed inspections (DET) to ensure that any 

visible cracks in the wing top skin panels 1 

and 2 along Rib 2 are detected in time and 

repaired appropriately. EASA issued [EASA] 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
61328 Federal Register / Vol. 80, No. 197 / Tuesday, October 13, 2015 / Proposed Rules 

AD 2008-0211 [http://ad.easa.europa.eu/ad/

2008-0211] to require implementation of this 

inspection programme. 

Since that [EASA] AD was issued, Airbus 

improved the inspection programme with an 

ultrasonic inspection to allow earlier crack 

detection, to subsequently reduce the scope 

of potential repair action, and to extend the 

intervals of the repetitive inspections. 

For the reasons described above, this 

[EASA] AD [http://ad.easa.europa.eu/ad/

2014-0200R1] retains the requirements of 

EASA AD 2008–0211, which is superseded, 

and requires supplementary repetitive 

ultrasonic inspections [for cracking] of the 

wing top skin panel 1 and 2 between STG2 

and STG10 at Rib 2 [and repair if needed]. 

* * * * * 

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– 

3985. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information: 

• Airbus Service Bulletin A310–57– 

2096, dated May 6, 2008, 

• Airbus Service Bulletin A310–57– 

2096, Revision 01, dated August 5, 

2010. 

• Airbus Service Bulletin A310–57– 

2096, Revision 02, dated March 5, 2014. 

This service information describes 

procedures for detailed visual and 

ultrasonic inspections for cracking 

around the fastener holes of the wing 

top skin panels between the right side 

and left side of the front and rear spars 

at certain locations, and repair if 

needed. 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. 

Explanation of ‘‘RC’’ Procedures and 

Tests in Service Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which procedures and tests 

in the service information are required 

for compliance with an AD. 

Differentiating these procedures and 

tests from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The procedures and tests 

identified as RC (required for 

compliance) in any service information 

have a direct effect on detecting, 

preventing, resolving, or eliminating an 

identified unsafe condition. 

As specified in a NOTE under the 

Accomplishment Instructions of the 

specified service information, 

procedures and tests that are identified 

as RC in any service information must 

be done to comply with the proposed 

AD. However, procedures and tests that 

are not identified as RC are 

recommended. Those procedures and 

tests that are not identified as RC may 

be deviated from using accepted 

methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of 

an alternative method of compliance 

(AMOC), provided the procedures and 

tests identified as RC can be done and 

the airplane can be put back in a 

serviceable condition. Any substitutions 

or changes to procedures or tests 

identified as RC will require approval of 

an AMOC. 

Costs of Compliance 

We estimate that this proposed AD 

affects 13 airplanes of U.S. registry. 

We also estimate that it would take 

about 5 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 $0 per product. Based 

on these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $5,525, or $425 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this 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) 

2010–04–03, Amendment 39–16196 (75 

FR 6852, February 12, 2010), and adding 

the following new AD: 

Airbus: Docket No. FAA–2015–3985; 

Directorate Identifier 2014–NM–182–AD. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 197 / Tuesday, October 13, 2015 / Proposed Rules 61329 

(a) Comments Due Date 

We must receive comments by November 

27, 2015. 

(b) Affected ADs 

This AD replaces AD 2010–04–03, 

Amendment 39–16196 (75 FR 6852, February 

12, 2010). 

(c) Applicability 

This AD applies to all Airbus Model A310– 

203, –204, –221, –222, –304, –322, –324, and 

–325 airplanes, certificated in any category, 

all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by cracking around 

the fastener holes in certain wing top skin 

panels between the right side and left side of 

the front and rear spars. This AD was also 

prompted by the development of an 

ultrasonic inspection program to allow for 

earlier crack detection and extend the 

repetitive inspection intervals. We are 

issuing this AD to detect and correct cracking 

around the fastener holes in certain wing top 

skin panels between the right side and left 

side of the front and rear spars, which could 

result in reduced structural integrity of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Except as required by paragraph (i) of this 

AD: Within the initial compliance time and 

thereafter at repetitive intervals specified in 

paragraphs (h)(1) through (h)(3) of this AD, 

as applicable, accomplish the actions 

specified in paragraphs (g)(1) and (g)(2) 

concurrently and in sequence, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A310–57–2096, 

Revision 02, dated March 5, 2014, except as 

provided by paragraph (j) of this AD. 

(1) Accomplish a detailed inspection for 

cracking around fastener holes in the wing 

top skin panels 1 and 2, along rib 2 between 

the front and rear spars on both the left-side 

and right-side of the fuselage. 

(2) Accomplish an ultrasonic inspection for 

cracking around fastener holes in the wing 

top skin panels 1 and 2, along rib 2, between 

stringer 2 and stringer 10 on the left-side and 

right-side of the fuselage. 

(h) Compliance Times for Airplanes Not 

Previously Inspected 

(1) For Model A310–203, –204, –221, and 

–222 airplanes: Do the actions required by 

paragraph (g)(1) and (g)(2) of this AD at the 

later of the times specified in paragraph 

(h)(1)(i) or (h)(1)(ii) of this AD. Repeat the 

inspections specified in paragraphs (g)(1) and 

(g)(2) of this AD thereafter at intervals not to 

exceed 2,000 flight cycles or 4,100 flight 

hours, whichever occurs first. 

(i) Prior to the accumulation of 18,700 

flight cycles or 37,400 flight hours since first 

flight of the airplane, whichever occurs first. 

(ii) Within 30 days after the effective date 

of this AD. 

(2) For Model A310–304, –322, –324, and 

–325 airplanes having an average flight time 

(AFT) of less than 4 hours: Do the actions 

required by paragraph (g)(1) and (g)(2) of this 

AD at the later of the times specified in 

paragraph (h)(2)(i) or (h)(2)(ii) of this AD. 

Repeat the inspections specified in 

paragraphs (g)(1) and (g)(2) of this AD 

thereafter at intervals not to exceed 2,000 

flight cycles or 5,600 flight hours, whichever 

occurs first. 

(i) Prior to the accumulation of 17,300 

flight cycles or 48,400 flight hours since first 

flight of the airplane, whichever occurs first. 

(ii) Within 30 days after the effective date 

of this AD. 

(3) For Model A310–304, –322, –324, and 

–325 airplanes having an AFT of equal to or 

more than 4 hours: Do the actions required 

by paragraph (g)(1) and (g)(2) of this AD at 

the later of the times specified in paragraph 

(h)(3)(i) or (h)(3)(ii) of this AD. Repeat the 

inspections specified in paragraphs (g)(1) and 

(g)(2) of this AD thereafter at intervals not to 

exceed 1,500 flight cycles or 7,500 flight 

hours, whichever occurs first. 

(i) Prior to the accumulation of 12,800 

flight cycles or 64,300 flight hours since first 

flight of the airplane, whichever occurs first. 

(ii) Within 30 days after the effective date 

of this AD. 

(i) Compliance Times of Airplanes 

Previously Inspected 

For airplanes previously inspected before 

the effective date of this AD using Airbus 

Service Bulletin A310–57–2096, dated May 

6, 2008; or Airbus Service Bulletin A310–57– 

2096, Revision 01, dated August 5, 2010: At 

the applicable compliance times specified in 

paragraphs (i)(1) through (i)(3) of this AD, 

accomplish the actions specified in 

paragraphs (g)(1) and (g)(2) concurrently and 

in sequence, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A310–57–2096, Revision 02, 

dated March 5, 2014. Repeat the inspections 

specified in paragraphs (g)(1) and (g)(2) of 

this AD, thereafter at the repetitive intervals 

specified in paragraphs (h)(1) through (h)(3) 

of this AD, as applicable. 

(1) For Model A310–203, –204, –221, and 

–222 airplanes: Do the actions required by 

paragraph (g)(1) and (g)(2) of this AD within 

3,500 flight hours or 1,700 flight cycles, 

whichever occurs first since the most recent 

inspection. 

(2) For Model A310–304, –322, –324, and 

–325 airplanes having an AFT of less than 4 

hours: Do the actions required by paragraph 

(g)(1) and (g)(2) of this AD within 4,600 flight 

hours or 1,600 flight cycles, whichever 

occurs first since the most recent inspection. 

(3) For Model A310–304, –322, –324, and 

–325 airplanes having an AFT of equal to or 

more than 4 hours: Do the actions required 

by paragraph (g)(1) and (g)(2) of this AD 

within 6,100 flight hours or 1,200 flight 

cycles, whichever occurs first since the most 

recent inspection. 

(j) Compliance Times if No Ultrasonic 

Equipment Is Available 

If no ultrasonic equipment is available for 

the initial or second inspection required by 

paragraph (g) or (h) of this AD, accomplish 

the detailed inspection specified in 

paragraph (g)(1) of this AD, within the 

applicable compliance times specified in 

paragraphs (j)(1) and (j)(2) of this AD. After 

accomplishing the detailed inspection, do the 

inspections specified in paragraphs (g)(1) and 

(g)(2) of this AD at the applicable compliance 

times specified by paragraphs (i)(1) through 

(i)(3) of this AD. Subsequently, repeat the 

inspections specified in paragraphs (g)(1) and 

(g)(2) of this AD thereafter at the applicable 

repetitive intervals specified in paragraphs 

(h)(1) through (h)(3) of this AD. 

(1) For airplanes not previously inspected 

before the effective date of this AD: Do the 

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

AD within the initial compliance time 

specified by paragraphs (h)(1) through (h)(3) 

of this AD, as applicable. 

(2) For airplanes previously inspected 

before the effective date of this AD using the 

service information identified in paragraph 

(j)(2)(i), (j)(2)(ii), or (j)(2)(iii) of this AD: Do 

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

this AD within the applicable compliance 

times specified in paragraphs (i)(1) through 

(i)(3) of this AD. 

(i) Airbus Service Bulletin A310–57–2096, 

dated May 6, 2008. 

(ii) Airbus Service Bulletin A310–57–2096, 

Revision 01, dated August 5, 2010. 

(iii) Airbus Service Bulletin A310–57– 

2096, Revision 02, dated March 5, 2014. 

(k) Repair of Cracking 

If any cracking is found during any 

inspection required by paragraphs (g), (h), (i), 

or (j) of this AD, before further flight, repair 

the cracking 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). 

(l) Terminating Action for Certain Repetitive 

Inspections 

Accomplishment of a repair using the 

service information identified in paragraph 

(l)(1), (l)(2), or (l)(3) of this AD, constitutes 

terminating action for the requirements of 

paragraph (g) of this AD, only for the repaired 

areas of the airplane. 

(1) Airbus Service Bulletin A310–57–2096, 

dated May 6, 2008. 

(2) Airbus Service Bulletin A310–57–2096, 

Revision 01, dated August 5, 2010. 

(3) Airbus Service Bulletin A310–57–2096, 

Revision 02, dated March 5, 2014. 

(m) Definition of Average Flight Time (AFT) 

For the purposes of this AD, the AFT 

should be established as specified in 

paragraphs (m)(1), (m)(2), and (m)(3) of this 

AD for the determination of the compliance 

times. 

(1) The inspection threshold is defined as 

the total flight hours accumulated (counted 

from take-off to touch-down), divided by the 

total number of flight cycles accumulated at 

the effective date of this AD. 

(2) The initial inspection interval is 

defined as the total flight hours accumulated 

divided by the total number of flight cycles 

accumulated at the time of the initial 

inspection threshold. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
61330 Federal Register / Vol. 80, No. 197 / Tuesday, October 13, 2015 / Proposed Rules 

(3) The second inspection interval is 

defined as the total flight hours accumulated 

divided by the total number of flight cycles 

accumulated between the initial and second 

threshold. 

(n) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g)(1) of this AD, if 

those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A310–57–2096, dated May 6, 2008; 

or Airbus Service Bulletin A310–57–2096, 

Revision 01, dated August 5, 2010. 

(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: 

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. 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: 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 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(3) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

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 procedures and tests identified as RC can 

be done and the airplane can be put back in 

a serviceable condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0200R1, dated 

September 19, 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–2015–3985. 

(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 

September 28, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–25758 Filed 10–9–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3661; Directorate 

Identifier 2015–NE–24–AD] 

RIN 2120–AA64 

Airworthiness Directives; Dowty 

Propellers Constant Speed Propellers 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Dowty Propellers R352/6–123–F/1, 

R352/6–123–F/2, and R410/6–123–F/35 

model propellers. This proposed AD 

was prompted by reports of dowel hole 

cracks in the face of the rear hub half. 

This proposed AD would require a 

records review to determine repair 

status and marking the affected 

propeller hubs as required. This 

proposed AD would also require 

installing dowel hole liners as 

necessary. We are proposing this AD to 

prevent loss of structural integrity of the 

propeller hub, which could result in 

damage to the propeller and damage to 

the airplane. 

DATES: We must receive comments on 

this proposed AD by December 14, 

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. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: 202–493–2251. 

For service information identified in 

this proposed AD, contact Dowty 

Propellers, 114 Powers Court, Sterling, 

VA 20166; phone: 703–421–4434; fax: 

703–450–0087; email: 

technicalsupport@dowty.com; Internet: 

www.http://dowty.com/services/repairand-overhaul. You may view this 

service information at the FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

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– 

3661; 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 

mandatory continuing airworthiness 

information (MCAI), the regulatory 

evaluation, any comments received, and 

other information. The 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: 

Michael Schwetz, Aerospace Engineer, 

Boston Aircraft Certification Office, 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA 01803; phone: 781– 

238–7761; fax 781–238–7170; email: 

michael.schwetz@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this NPRM. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–3661; Directorate Identifier 2015– 

NE–24–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this NPRM. We will consider 

all comments received by the closing 

date and may amend this NPRM 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 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS