19248 Federal Register / Vol. 80, No. 69 / Friday, April 10, 2015 / Proposed Rules 

the MLG with a serviceable MLG as 

identified in paragraph (j) of this AD, using 

a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or ATR–GIE 

Avions de Transport Re ́gional’s EASA Design 

Organization Approval (DOA). 

(1) No later than the next MLG overhaul 

scheduled after the effective date of this AD. 

(2) Within 20,000 flight cycles or 9 years, 

whichever occurs first, accumulated since 

installation of the MLG on an airplane since 

new or since last overhaul, as applicable. 

(j) Definition of Serviceable MLG for Model 

ATR72 Airplanes 

For Model ATR72 airplanes: For purposes 

of paragraph (i) of this AD, a serviceable MLG 

is one that incorporates pins specified in 

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

(1) Pins that are not identified in MessierBugatti-Dowty Service Bulletin 631–32–214, 

dated January 13, 2014; or Messier-BugattiDowty Service Bulletin 631–32–219, dated 

March 3, 2014; as applicable. 

(2) Pins that have been inspected and 

reconditioned in accordance with the 

Accomplishment Instructions of MessierBugatti-Dowty Service Bulletin 631–32–214, 

dated January 13, 2014; or Messier-BugattiDowty Service Bulletin 631–32–219, dated 

March 3, 2014; as applicable. 

(k) MLG Pin Identification and Replacement 

for Model ATR42 Airplanes 

(1) For Model ATR42 airplanes: Within the 

compliance time identified in paragraph 

(k)(1)(i) or (k)(1)(ii) of this AD, whichever 

occurs first, inspect for any LH and RH MLG 

pins having a part number and serial number 

listed in Messier-Bugatti-Dowty Service 

Bulletin 631–32–215, dated January 13, 2014; 

or Messier-Bugatti-Dowty Service Bulletin 

631–32–220, dated March 3, 2014; as 

applicable. A review of airplane maintenance 

records is acceptable in lieu of this 

identification if the part number and serial 

number of the LH and RH MLG pin can be 

conclusively determined from that review. 

(i) No later than the next MLG overhaul 

scheduled after the effective date of this AD. 

(ii) Within 20,000 flight cycles or 9 years, 

whichever occurs first, accumulated since 

installation of the MLG on an airplane since 

new or since last overhaul, as applicable. 

(2) If the MLG pin having a part number 

and serial number listed in Messier- BugattiDowty Service Bulletin 631–32–215, dated 

January 13, 2014; or Messier-Bugatti-Dowty 

Service Bulletin 631–32–220, dated March 3, 

2014; as applicable; is found to be installed 

during the identification required by 

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

compliance time identified in paragraph 

(k)(1) of this AD, replace the MLG with a 

serviceable MLG, using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or ATR–GIE Avions de Transport 

Re ́gional’s EASA DOA. A serviceable MLG is 

a part that has pins as identified in paragraph 

(k)(2)(i) or (k)(2)(ii) of this AD. 

(i) Pins that are not listed in MessierBugatti-Dowty Service Bulletin 631–32–215, 

dated January 13, 2014; or Messier-BugattiDowty Service Bulletin 631–32–220, dated 

March 3, 2014; as applicable. 

(ii) Pins that have been inspected and 

reconditioned, in accordance with the 

Accomplishment Instructions of MessierBugatti-Dowty Service Bulletin 631–32–215, 

dated January 13, 2014; or Messier-BugattiDowty Service Bulletin 631–32–220, dated 

March 3, 2014; as applicable. 

(l) Credit for Previous Actions 

This paragraph provides credit for actions 

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

actions were performed before the effective 

date of this AD using Messier-Bugatti-Dowty 

Service Bulletin 631–32–216, dated October 

30, 2013, which is not incorporated by 

reference in this AD. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; fax 425–227–1149. 

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 

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 ATR–GIE Avions de Transport 

Re ́gional’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0074, dated 

March 21, 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– 

2015–0682. 

(2) For Messier-Bugatti-Dowty service 

information identified in this AD, contact 

ATR–GIE Avions de Transport Re ́gional, 1, 

Alle ́e Pierre Nadot, 31712 Blagnac Cedex, 

France; telephone +33 (0) 5 62 21 62 21; fax 

+33 (0) 5 62 21 67 18; email 

continued.airworthiness@atr.fr; Internet 

http://www.aerochain.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 March 

25, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–07801 Filed 4–9–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0683; Directorate 

Identifier 2014–NM–196–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 all The 

Boeing Company Model 767–200, –300, 

and –300F series airplanes. This 

proposed AD was prompted by a finding 

that certain barrel nuts installed at the 

vertical fin may be subject to stress 

corrosion and cracking. This proposed 

AD would require either repetitive 

inspections of vertical fin barrel nuts for 

corrosion or a magnetic check to 

identify certain barrel nuts, and 

corrective actions if necessary. We are 

proposing this AD to detect and correct 

corroded and loose barrel nuts that 

attach the vertical fin to body section 

48, which could result in reduced 

structural integrity of the vertical fin 

attachment joint, loss of the vertical fin, 

and consequent loss of controllability of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by May 26, 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. 


rljohnson on DSK3VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 69 / Friday, April 10, 2015 / Proposed Rules 19249 

For service information identified in 

this proposed 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA 2015– 

0683. 

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– 

0683; 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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6577; 

fax: 425–917–6590; email: 

berhane.alazar@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– 

2015–0683; Directorate Identifier 2014– 

NM–196–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 May 16, 2003, we issued AD 

2003–10–11, Amendment 39–13156 (68 

FR 28703, May 27, 2003), to require 

replacement of H–11 steel barrel nuts 

with new Inconel barrel nuts, because of 

possible corrosion and cracking. AD 

2003–10–11 applied to Model 767–200 

and –300 airplanes, line numbers 1 

through 574 inclusive. 

We have received a report of H–11 

steel barrel nuts installed on an airplane 

not included in the applicability of AD 

2003–10–11, Amendment 39–13156 (68 

FR 28703, May 27, 2003). Further 

investigation has revealed that airplanes 

with line numbers 575 through 681 had 

either H–11 steel or Inconel barrel nuts 

installed at the 16 vertical fin 

attachment points. Galvanic corrosion 

can occur on H–11 steel barrel nuts if 

moisture is present. This condition, if 

not corrected, could result in failure of 

the H–11 steel barrel nuts that attach the 

vertical fin to body section 48, which 

could result in reduced structural 

integrity of the vertical fin attachment 

joint, loss of the vertical fin, and 

consequent loss of controllability of the 

airplane. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 767–53A0261, dated August 12, 

2014. The service information describes 

procedures for repetitive inspections of 

vertical fin barrel nuts for corrosion or 

a magnetic check to identify certain 

barrel nuts, and corrective actions if 

necessary. Refer to this service 

information for information on the 

procedures and compliance times. This 

service information is reasonably 

available; see ADDRESSES for ways to 

access this service information. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information identified 

previously. 

Explanation of ‘‘RC (Required for 

Compliance)’’ Steps in Service 

Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (AD ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which steps in the service 

information are required for compliance 

with an AD. Differentiating these steps 

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 actions specified in the 

service information identified 

previously include steps that are 

identified as RC because these steps 

have a direct effect on detecting, 

preventing, resolving, or eliminating an 

identified unsafe condition. 

Steps that are identified as RC in any 

service information must be done to 

comply with the proposed AD. 

However, steps that are not identified as 

RC are recommended. Those steps 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 steps identified 

as RC can be done and the airplane can 

be put back in a serviceable condition. 

Any substitutions or changes to steps 

identified as RC will require approval of 

an AMOC. 

Costs of Compliance 

We estimate that this proposed AD 

affects 38 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Option 1: Detailed inspections and torque 

check.

4 work-hours × $85 per hour = $340 per inspection cycle.

1 Up to $482,661 per 

inspection cycle.

Up to $18,341,118. 


rljohnson on DSK3VPTVN1PROD with PROPOSALS
19250 Federal Register / Vol. 80, No. 69 / Friday, April 10, 2015 / Proposed Rules 

ESTIMATED COSTS—Continued 

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Option 2: Magnetic check 4 work-hours × $85 per hour = $340 ..................... $0 $340 .......................... Up to $12,920. 

1For the torque check, operators may choose to rent a special tool, with rental costs up to $482,321. 

We estimate that replacing any barrel 

nut would take 1 work-hour, at an 

average labor rate of $85 per work-hour. 

We have received no definitive data that 

would enable us to provide cost 

estimates for the cost of replacement 

parts. We have no way of determining 

the number of aircraft that might need 

these replacements. 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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): 

The Boeing Company: Docket No. FAA– 

2015–0683; Directorate Identifier 2014– 

NM–196–AD. 

(a) Comments Due Date 

We must receive comments by May 26, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 767–200, –300, and –300F 

series airplanes, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a finding that 

certain barrel nuts installed at the vertical fin 

may be subject to stress corrosion and 

cracking. We are issuing this AD to detect 

and correct cracked, corroded, or broken 

barrel nuts that attach the vertical fin to body 

section 48, which could result in reduced 

structural integrity of the vertical fin 

attachment joint, loss of the vertical fin, and 

consequent loss of controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

For airplanes identified in Boeing Alert 

Service Bulletin 767–53A0261, dated August 

12, 2014: Do the actions specified in 

paragraph (g)(1) or (g)(2) of this AD, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–53A0261, dated August 12, 2014. Signs 

of corrosion include, but are not limited to, 

sealant cracks, sealant bulging, powder 

residue, and cracked barrel nuts. 

(1) At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 767–53A0261, dated 

August 12, 2014, except as provided by 

paragraph (h) of this AD: Do internal and 

external detailed inspections of the barrel 

nuts and sealant for signs of corrosion, and 

do a torque check of the vertical stabilizer 

attachment bolts for loose barrel nuts. 

(i) If corrosion or any loose barrel nut is 

found at any attachment point location, 

before further flight, replace the barrel nut 

with a new Inconel barrel nut. 

(ii) If no corrosion or loose barrel nut is 

found at any attachment point location, do 

the actions specified in paragraphs 

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

(A) Repeat the inspections and torque 

check thereafter at intervals not to exceed 18 

months until the replacement specified in 

paragraph (g)(1)(ii)(B) of this AD is done at 

that attachment point location. 

(B) Within 36 months after the effective 

date of this AD, replace all barrel nuts with 

new Inconel barrel nuts. 

(2) At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 767–53A0261, dated 

August 12, 2014, except as provided by 

paragraph (h) of this AD: Do a magnetic 

check to identify H–11 steel barrel nuts. 

(i) If any H–11 steel barrel nut is found at 

any attachment point location, before further 

flight, do an internal and external detailed 

inspection of the barrel nut holes and sealant 

for signs of corrosion, and do a torque check 

of the vertical stabilizer attachment bolts for 

loose barrel nuts. 

(A) If corrosion or any loose barrel nut is 

found, before further flight, replace the barrel 

nut with a new Inconel barrel nut. 

(B) If no corrosion or loose barrel nut is 

found, do the actions specified in paragraphs 

(g)(2)(i)(B)(1) and (g)(2)(i)(B)(2) of this AD. 

(1) Repeat the inspections and torque 

check thereafter at intervals not to exceed 18 

months until the replacement specified in 

paragraph (g)(2)(i)(B)(2) of this AD is done at 

that attachment point location. 


rljohnson on DSK3VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 69 / Friday, April 10, 2015 / Proposed Rules 19251 

(2) Within 36 months after the effective 

date of this AD, replace all H–11 steel barrel 

nuts with new Inconel barrel nuts. 

(ii) If no H–11 steel barrel nut is found at 

all attachment point locations, no further 

work is required by this paragraph. 

(h) Exception to Service Information 

Specifications 

Where Boeing Alert Service Bulletin 767– 

53A0261, dated August 12, 2014, specifies a 

compliance time ‘‘after the Original Issue 

date of this Service Bulletin,’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(i) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install an H–11 steel barrel nut 

on the vertical stabilizer of any airplane. 

(j) 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 (k)(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 

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 must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) If any service information contains 

steps that are identified as RC, those steps 

must be done to comply with this AD; any 

steps that are not identified as RC are 

recommended. Those steps 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 steps identified as RC 

can be done and the airplane can be put back 

in a serviceable condition. Any substitutions 

or changes to steps identified as RC require 

approval of an AMOC. 

(k) Related Information 

(1) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6577; fax: 425–917–6590; 

email: berhane.alazar@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 March 

24, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–08072 Filed 4–9–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 121 

[Docket No. FAA–2015–0881] 

Interpretation of the Flight Time 

Limitations 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of Proposed 

Interpretation 

SUMMARY: This action proposes to 

interpret our regulations to not apply to 

flight segments that are flown by a 

flightcrew consisting of only two pilots 

and no other flight crewmembers. 

DATES: Comments must be received on 

or before May 11, 2015. 

ADDRESSES: You may send comments 

identified by docket number FAA– 

2015–0881 using any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the online instructions for sending your 

comments electronically. 

• Mail: Send Comments to Docket 

Operations, M–30; US Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, West Building 

Ground Floor, Washington, DC 20590– 

0001. 

• Hand Delivery: Take comments to 

Docket Operations in Room W12–140 of 

the West Building Ground Floor at 1200 

New Jersey Avenue SE., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

• Fax: (202) 493–2251. 

FOR FURTHER INFORMATION CONTACT: Alex 

Zektser, Attorney, Regulations Division, 

Office of Chief Counsel, Federal 

Aviation Administration, 800 

Independence Avenue SW., 

Washington, DC 20591; telephone: (202) 

267–8018; email: Alex.Zektser@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA invites interested persons to 

submit written comments, data, or 

views concerning this proposal. The 

most helpful comments reference a 

specific portion of the proposal, explain 

the reason for any recommended 

change, and include supporting data. To 

ensure the docket does not contain 

duplicate comments, please send only 

one copy of written comments, or if you 

are filing comments electronically, 

please submit your comments only one 

time. 

The FAA will file in the docket all 

comments received, as well as a report 

summarizing each substantive public 

contact with FAA personnel concerning 

this proposal. Before acting on this 

proposal, the FAA will consider all 

comments received on or before the 

closing date for comments and any latefiled comments if it is possible to do so 

without incurring expense or delay. The 

FAA may change this proposal in light 

of comments received. 

Availability of This Proposed 

Interpretation 

You can get an electronic copy using 

the Internet by— 

(1) Searching the Federal 

eRulemaking Portal (http://

www.regulations.gov); 

(2) Visiting the FAA’s Regulations and 

Policies Web page at http://

www.faa.gov/regulations_policies/; or 

(3) Accessing the Government 

Publishing Office’s Web page at http:// 

www.gpoaccess.gov/fr/index.html. 

You can also get a copy by sending a 

request to the Federal Aviation 

Administration, Office of Rulemaking, 

ARM–1, 800 Independence Avenue 

SW., Washington, DC 20591, or by 

calling (202) 267–9680. Make sure to 

identify the docket number or notice 

number of this proposal. 

Background 

The FAA has been asked to provide 

two legal interpretations regarding the 

application of 14 CFR 121.521. 

Specifically, both interpretation 

requests present scenarios involving 

supplemental all-cargo part 121 

operations that contain at least one 

international segment and make an 

election, under 14 CFR 121.513, to 

operate under the flight time limitations 

of § 121.515 and §§ 121.521 through 

121.525. 

Both scenarios involve, in part, at 

least one segment in which the aircraft 

would be flown by a flightcrew 

consisting solely of two pilots and no 

other flight crewmembers. Both 


rljohnson on DSK3VPTVN1PROD with PROPOSALS