38036 Federal Register / Vol. 80, No. 127 / Thursday, July 2, 2015 / Proposed Rules 

Issued in Renton, Washington, on June 24, 

2015. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–16155 Filed 7–1–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1991; Directorate 

Identifier 2014–NM–251–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Model A318–111 and –112 

airplanes; Model A319–111, –112, and 

–115 airplanes; Model A320–214 

airplanes; and Model A321–111, –112, 

–211, –212, and –213 airplanes. This 

proposed AD was prompted by reports 

of cracked cadmium-plated lock nuts 

that attach the hinge to the fan cowl 

door. This proposed AD would require 

inspecting to determine the serial 

number of each engine fan cowl door, 

inspecting for cracking of the hinge lock 

nuts of any affected door, and replacing 

the lock nuts if necessary. We are 

proposing this AD to detect and correct 

cracking of the hinge lock nuts, which 

could result in separation of the hinge 

from the fan cowl door, in-flight loss of 

the door, and consequent damage to the 

airplane. 

DATES: We must receive comments on 

this proposed AD by August 17, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact the following: 

For Airbus service information 

contact Airbus, Airworthiness Office— 

EIAS, 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.airwortheas@airbus.com; Internet http://

www.airbus.com. 

For Goodrich service information 

contact Goodrich Aerostructures, 850 

Lagoon Drive, Chula Vista, California, 

91910–2098; telephone: 619–691–2719; 

email: jan.lewis@goodrich.com; Internet: 

http://www.goodrich.com/TechPubs. 

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– 

1991; 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone: 425–227–1405; 

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–2015–1991; Directorate Identifier 

2014–NM–251–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0276, dated December 

19, 2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for all Airbus 

Model A318–111 and –112 airplanes; 

Model A319–111, –112, and –115 

airplanes; Model A320–214 airplanes; 

and Model A321–111, –112, –211, –212, 

and –213 airplanes. The MCAI states: 

In-service findings have been reported of 

cracked cadmium plated lock nuts. This 

cracking occurs shortly after installation. 

Investigation results attribute the cause to an 

improper manufacturing procedure of the 

nuts. It was determined that the affected 

batch of lock nuts was used on the fan cowl 

to attach hinges to the cowl doors on 

CFM56–5B engines only. 

This condition, if not corrected, could lead 

to separation of the hinge from the fan cowl 

door, possibly resulting in in-flight loss of a 

fan cowl door, with consequent damage to 

the aeroplane and/or injury to persons on the 

ground. 

For the reasons describes above, this 

[EASA] AD required identification of the 

affected fan cowl doors, a one-time 

inspection of the fan cowl door hinge nuts 

and, depending on findings, replacement of 

the affected nuts. 

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– 

1991. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–71–1062, including Appendix 01, 

dated July 28, 2014. Goodrich 

Aerostructures has issued Service 

Bulletin RA32071–151, dated June 11, 

2014. The service information describes 

procedures for inspection of the hinge 

nuts of the fan cowl door, and 

replacement if necessary. 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 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 127 / Thursday, July 2, 2015 / Proposed Rules 38037 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 437 airplanes of U.S. registry. 

We also estimate that it would take 

about 2 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $0 per product. 

Based on these figures, we estimate the 

cost of this proposed AD on U.S. 

operators to be $74,290, or $170 per 

product. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this proposed AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2015–1991; 

Directorate Identifier 2014–NM–251–AD. 

(a) Comments Due Date 

We must receive comments by August 17, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

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

of this AD, certificated in any category, all 

manufacturer serial numbers. 

(1) Airbus Model A318–111 and –112 

airplanes. 

(2) Airbus Model A319–111, –112, and 

–115 airplanes. 

(3) Airbus Model A320–214 airplanes. 

(4) Airbus Model A321–111, –112, –211, 

212, and –213 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Powerplant. 

(e) Reason 

This AD was prompted by reports of 

cracked cadmium-plated lock nuts that attach 

the hinge to the fan cowl door. We are 

issuing this AD to detect and correct cracking 

of the hinge lock nuts, which could result in 

separation of the hinge from the fan cowl 

door, the in-flight loss of the door, and 

consequent damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspect To Determine Serial Number 

Within 24 months after the effective date 

of this AD: Inspect to determine if any fan 

cowl door has a serial number 10029001 

through 11092003 inclusive, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–71–1062, 

dated July 28, 2014; or Goodrich 

Aerostructures Service Bulletin RA32071– 

151, dated June 11, 2014. A review of 

airplane maintenance records is acceptable in 

lieu of the inspection required by this 

paragraph, provided those records can be 

relied upon for that purpose and the serial 

number can be positively identified by that 

review. 

(h) Inspection and Replacement 

For any fan cowl door having any serial 

number identified in paragraph (g) of this 

AD: Within 24 months after the effective date 

of this AD, do a detailed inspection for 

cracking of the hinge lock nuts of the door, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

71–1062, dated July 28, 2014; or Goodrich 

Aerostructures Service Bulletin RA32071– 

151, dated June 11, 2014. If any crack is 

found, before further flight, replace each 

cracked hinge lock nut, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–71–1062, dated July 

28, 2014; or Goodrich Aerostructures Service 

Bulletin RA32071–151, dated June 11, 2014. 

(i) Special Flight Permits 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–227–1405; fax: 425–227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
38038 Federal Register / Vol. 80, No. 127 / Thursday, July 2, 2015 / Proposed Rules 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0276, dated 

December 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–2015–1991. 

(2) For Airbus service information contact 

Airbus, Airworthiness Office—EIAS, 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. 

(3) For Goodrich service information 

contact Goodrich Aerostructures, 850 Lagoon 

Drive, Chula Vista, California, 91910–2098; 

telephone: 619–691–2719; email: jan.lewis@

goodrich.com; Internet: http://

www.goodrich.com/TechPubs. 

(4) 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 June 24, 

2015. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–16165 Filed 7–1–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2455; Directorate 

Identifier 2014–NM–180–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 supersede 

Airworthiness Directive (AD) 2008–26– 

07, which applies to all McDonnell 

Douglas Model DC–8–11, DC–8–12, DC– 

8–21, DC–8–31, DC–8–32, DC–8–33, 

DC–8–41, DC–8–42, and DC–8–43 

airplanes; Model DC–8–50 series 

airplanes; Model DC–8F–54 and DC– 

8F–55 airplanes; Model DC–8–60 series 

airplanes; Model DC–8–60F series 

airplanes; Model DC–8–70 series 

airplanes; and Model DC–8–70F series 

airplanes. AD 2008–26–07 currently 

requires repetitive inspections of the 

lower skin and stringers at certain 

stations, and corrective actions if 

necessary. This proposed AD is 

intended to complete certain mandated 

programs intended to support the 

airplane reaching its limit of validity 

(LOV) of the engineering data that 

support the established structural 

maintenance program. This proposed 

AD would also require an eddy current 

high frequency (ETHF) inspection for 

cracks of the fastener open holes 

common to the lower skins, stringers, 

and splice fittings at a certain station; 

installation of external doublers and 

fasteners and repetitive eddy current 

low frequency (ETLF) inspections 

around the fasteners for any crack; and 

corrective actions if necessary. We are 

proposing this AD to detect and correct 

cracks in the lower skins, stringers, and 

fastener holes of the splice fittings, 

which could result in the loss of 

structural integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by August 17, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: 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. For information on the 

availability of this material at the FAA, 

call 425–227–1221. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

2455. 

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– 

2455; 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: 

Chandra Ramdoss, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; telephone: 

562–627–5239; fax: 562–627–5210; 

email: Chandraduth.Ramdoss@faa.gov. 

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–2015–2455; Directorate Identifier 

2014–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 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. 

Discussion 

On December 12, 2008, we issued AD 

2008–26–07, Amendment 39–15773 (73 

FR 78946, December 24, 2008), for all 

McDonnell Douglas Model DC–8–11, 

DC–8–12, DC–8–21, DC–8–31, DC–8–32, 

DC–8–33, DC–8–41, DC–8–42, and DC– 

8–43 airplanes; Model DC–8–50 series 

airplanes; Model DC–8F–54 and DC– 

8F–55 airplanes; Model DC–8–60 series 

airplanes; Model DC–8–60F series 

airplanes; Model DC–8–70 series 

airplanes; and Model DC–8–70F series 

airplanes. AD 2008–26–07 requires 

repetitive inspections of the lower skin 

and stringers at stations Xw=408 and 

Xw=-408, and corrective actions if 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS