Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules 74731 

a pylon and consequent reduced structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

At the later of times specified in 

paragraphs (g)(1) and (g)(2), or (g)(1) and 

(g)(3), of this AD, as applicable: Do a detailed 

inspection for damage and cracking of the 

AFF of the pylons, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–54–1027, dated April 

10, 2014. Repeat the inspection thereafter at 

intervals not to exceed 2,500 flight cycles or 

3,750 flight hours, whichever occurs first. 

(1) For all airplanes: Before exceeding 

5,000 flight cycles or 7,500 flight hours, 

whichever occurs first since the airplane’s 

first flight. 

(2) For airplanes on which the inspection 

specified in Airbus All Operators 

Transmission (AOT) A54N002–12 has been 

done as of the effective date of this AD: 

Within 2,500 flight cycles or 3,750 flight 

hours, since the most recent accomplishment 

of maintenance planning document (MPD) 

Task ZL 371–01, or since doing the most 

recent inspection specified in Airbus AOT 

A54N002–12, whichever occurs first. 

(3) For airplanes on which the inspection 

specified in Airbus AOT A54N002–12 has 

not been done as of the effective date of this 

AD: Within 750 flight cycles or 1,500 flight 

hours after the effective date of this AD, 

whichever occurs first. 

(h) Repair 

If any crack is found during any inspection 

required by paragraph (g) of this AD; before 

further flight, repair in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–54–1027, dated April 

10, 2014. Accomplishment of this repair does 

not terminate the repetitive inspections 

required by paragraph (g) of this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 

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. 

(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 an 

airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0154, dated 

July 2, 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– 

2015–6537. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 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 20, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–30218 Filed 11–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–6538; Directorate 

Identifier 2015–NM–031–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–100, 

–200, –200C, –300, –400, and –500 

series airplanes. This proposed AD was 

prompted by an evaluation by the 

design approval holder (DAH) 

indicating that the bulkhead is subject 

to widespread fatigue damage (WFD). 

This proposed AD would require 

repetitive inspections of the aft pressure 

bulkhead web for any cracking, 

incorrectly drilled fastener holes, and 

elongated fastener holes, and related 

investigative and corrective actions if 

necessary. We are proposing this AD to 

detect and correct fatigue cracking of the 

aft pressure bulkhead web at the ‘‘Y’’- 

chord, which could result in reduced 

structural integrity of the airplane and 

rapid decompression of the fuselage. 

DATES: We must receive comments on 

this proposed AD by January 14, 2016. 

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, 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– 

6538. 

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– 

6538; or in person at the Docket 

Management Facility between 9 a.m. 


jstallworth on DSK7TPTVN1PROD with PROPOSALS
74732 Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules 

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: 

Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

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

WA 98057–3356; telephone: 425–917– 

6450; fax: 425–917–6590; email: 

Alan.Pohl@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– 

2015–6538; Directorate Identifier 2015– 

NM–031–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 

Structural fatigue damage is 

progressive. It begins as minute cracks, 

and those cracks grow under the action 

of repeated stresses. This can happen 

because of normal operational 

conditions and design attributes, or 

because of isolated situations or 

incidents such as material defects, poor 

fabrication quality, or corrosion pits, 

dings, or scratches. Fatigue damage can 

occur locally, in small areas or 

structural design details, or globally. 

Global fatigue damage is general 

degradation of large areas of structure 

with similar structural details and stress 

levels. Multiple-site damage is global 

damage that occurs in a large structural 

element such as a single rivet line of a 

lap splice joining two large skin panels. 

Global damage can also occur in 

multiple elements such as adjacent 

frames or stringers. Multiple-sitedamage and multiple-element-damage 

cracks are typically too small initially to 

be reliably detected with normal 

inspection methods. Without 

intervention, these cracks will grow, 

and eventually compromise the 

structural integrity of the airplane, in a 

condition known as widespread fatigue 

damage (WFD). As an airplane ages, 

WFD will likely occur, and will 

certainly occur if the airplane is 

operated long enough without any 

intervention. 

The FAA’s WFD final rule (75 FR 

69746, November 15, 2010) became 

effective on January 14, 2011. The WFD 

rule requires certain actions to prevent 

structural failure due to WFD 

throughout the operational life of 

certain existing transport category 

airplanes and all of these airplanes that 

will be certificated in the future. For 

existing and future airplanes subject to 

the WFD rule, the rule requires that 

DAHs establish a limit of validity (LOV) 

of the engineering data that support the 

structural maintenance program. 

Operators affected by the WFD rule may 

not fly an airplane beyond its LOV, 

unless an extended LOV is approved. 

The WFD rule (75 FR 69746, 

November 15, 2010) does not require 

identifying and developing maintenance 

actions if the DAHs can show that such 

actions are not necessary to prevent 

WFD before the airplane reaches the 

LOV. Many LOVs, however, do depend 

on accomplishment of future 

maintenance actions. As stated in the 

WFD rule, any maintenance actions 

necessary to reach the LOV will be 

mandated by airworthiness directives 

through separate rulemaking actions. 

In the context of WFD, this action is 

necessary to enable DAHs to propose 

LOVs that allow operators the longest 

operational lives for their airplanes, and 

still ensure that WFD will not occur. 

This approach allows for an 

implementation strategy that provides 

flexibility to DAHs in determining the 

timing of service information 

development (with FAA approval), 

while providing operators with certainty 

regarding the LOV applicable to their 

airplanes. 

We have received an evaluation by 

the design approval holder (DAH) 

indicating that the aft pressure bulkhead 

is subject to WFD. Cracks have been 

reported in the aft pressure bulkhead 

web at the web-to-‘‘Y’’-chord interface 

and have occurred in the aft row of 

fasteners connecting the aft pressure 

bulkhead web to the ‘‘Y’’-chord. This 

condition, if not corrected, could result 

in fatigue cracking of the aft pressure 

bulkhead web at the ‘‘Y’’-chord, which 

could result in reduced structural 

integrity of the airplane and rapid 

decompression of the fuselage. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 737–53A1214, Revision 5, 

dated January 30, 2015. This service 

information describes, among other 

actions, procedures for repetitive 

inspections of the aft pressure bulkhead 

web for any cracking, incorrectly drilled 

fastener holes, and elongated fastener 

holes; and related investigative and 

corrective actions. 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 AD. 

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 described 

previously, except as discussed under 

‘‘Differences Between this Proposed AD 

and the Service Information.’’ Refer to 

this service information for details on 

the procedures and compliance times. 

The phrase ‘‘related investigative 

actions’’ is used in this proposed AD. 

‘‘Related investigative actions’’ are 

follow-on actions that (1) are related to 

the primary action, and (2) further 

investigate the nature of any condition 

found. Related investigative actions in 

an AD could include, for example, 

inspections. 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 

actions’’ correct or address any 

condition found. Corrective actions in 

an AD could include, for example, 

repairs. 

Differences Between This Proposed AD 

and the Service Information 

AD 2012–18–13 R1, Amendment 39– 

17429 (78 FR 27020, May 9, 2013), 

refers to Boeing Alert Service Bulletin 

737–53A1214, Revision 4, dated 

December 16, 2011, as an appropriate 

source of service information for doing 

certain actions required by that AD. 

Since AD 2012–18–13 R1 was issued, 

Boeing issued Alert Service Bulletin 

737–53A1214, Revision 5, dated January 

30, 2015, to address WFD by adding 

new inspections specified in tables 9, 

10, and 11 of paragraph 1.E., 


jstallworth on DSK7TPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules 74733 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 5, 

dated January 30, 2015. Boeing 

determined that the WFD-based 

inspections specified in tables 9, 10, and 

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

Boeing Alert Service Bulletin 737– 

53A1214, Revision 5, dated January 30, 

2015, affect only Group 2 airplanes 

because Group 1 airplanes will reach 

their limit of validity before the 

compliance times specified in tables 9, 

10, and 11 (Group 1 is for airplanes 

having line numbers 1 through 2565; 

Group 2 is for airplanes having line 

numbers 2566 through 3132). 

Therefore, although Boeing Alert 

Service Bulletin 737–53A1214, Revision 

5, dated January 30, 2015, is effective for 

all The Boeing Company Model 737– 

100, –200, –200C, –300, –400, and –500 

series airplanes, this proposed AD 

applies to only certain The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes 

(i.e., Group 2 airplanes). This difference 

is due to the fact that this proposed AD 

only addresses the new WFD 

inspections specified in Boeing Alert 

Service Bulletin 737–53A1214, Revision 

5, dated January 30, 2015. 

Accomplishing the actions required 

by paragraphs (g) and (h) of this 

proposed AD would terminate the 

inspections required by paragraphs (k) 

and (l) of AD 2012–18–13 R1, 

Amendment 39–17429 (78 FR 27020, 

May 9, 2013). 

The service bulletin specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

affects 122 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 

Inspections of the web 

at the ‘‘Y’’-chord.

Up to 60 work-hours × $85 per 

hour = Up to $5,100 per inspection cycle.

$0 Up to $5,100 per inspection cycle Up to $622,200 

per inspection cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates 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): 

The Boeing Company: Docket No. FAA– 

2015–6538; Directorate Identifier 2015– 

NM–031–AD. 

(a) Comments Due Date 

We must receive comments by January 14, 

2016. 

(b) Affected ADs 

This AD affects AD 2012–18–13 R1, 

Amendment 39–17429 (78 FR 27020, May 9, 

2013). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–100, –200, –200C, –300, –400, 

and –500 series airplanes, certificated in any 

category, identified as Group 2 in Boeing 

Alert Service Bulletin 737–53A1214, 

Revision 5, dated January 30, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder indicating that 

the aft pressure bulkhead is subject to 

widespread fatigue damage. We are issuing 

this AD to detect and correct fatigue cracking 

of the aft pressure bulkhead web at the ‘‘Y’’- 

chord, which could result in reduced 

structural integrity of the airplane and rapid 

decompression of the fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 


jstallworth on DSK7TPTVN1PROD with PROPOSALS
74734 Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules 

(g) Repetitive Inspections of the Aft Pressure 

Bulkhead Web at the ‘‘Y’’-Chord Upper 

Bulkhead 

At the applicable time specified in tables 

9 and 10 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1214, 

Revision 5, dated January 30, 2015: Do 

detailed and low frequency eddy current 

(LFEC) inspections from the aft side of the aft 

pressure bulkhead web, or do detailed and 

high frequency eddy current (HFEC) 

inspections from the forward side of the aft 

pressure bulkhead web, for any cracking, 

incorrectly drilled fastener hole, and 

elongated fastener hole, and do all applicable 

related investigative and corrective actions, 

in accordance with Part I of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1214, Revision 5, 

dated January 30, 2015, except as required by 

paragraph (i) of this AD. Do all related 

investigative and corrective actions before 

further flight. If any cracking, incorrectly 

drilled fastener hole, or elongated fastener 

hole is found, before further flight, repair the 

web using a method approved in accordance 

with the procedures specified in paragraph 

(l) of this AD. Thereafter, repeat the 

inspections at the applicable times specified 

in tables 9 and 10 of paragraph 1.E., 

‘‘Compliance’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 5, dated 

January 30, 2015. 

(h) Repetitive Inspections of the Aft Pressure 

Bulkhead Web at the ‘‘Y’’-Chord Below S–15 

At the applicable time specified in table 11 

of 1.E., ‘‘Compliance’’ of Boeing Alert Service 

Bulletin 737–53A1214, Revision 5, dated 

January 30, 2015: Do detailed and eddy 

current inspections of the web from the 

forward or aft side of the bulkhead for any 

cracking, incorrectly drilled fastener hole, 

and elongated fastener hole, and do all 

applicable corrective actions, in accordance 

with Part III of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1214, Revision 5, dated January 30, 

2015, except as required by paragraph (i) of 

this AD. Do all corrective actions before 

further flight. If any cracking, incorrectly 

drilled fastener hole, or elongated fastener 

hole is found, before further flight, repair the 

web using a method approved in accordance 

with the procedures specified in paragraph 

(l) of this AD. Thereafter, repeat the 

inspections at the applicable times specified 

in table 11 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Alert Service Bulletin 737– 

53A1214, Revision 5, dated January 30, 2015. 

(i) Exception to the Service Information 

Where Boeing Alert Service Bulletin 737– 

53A1214, Revision 5, dated January 30, 2015, 

specifies to contact Boeing for repair 

instructions: Before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (l) of 

this AD. 

(j) Terminating Action for Other Rulemaking 

Accomplishing the actions required by 

paragraphs (g) and (h) of this AD terminates 

the inspections required by paragraphs (k) 

and (l) of AD 2012–18–13 R1, Amendment 

39–17429 (78 FR 27020, May 9, 2013). 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g) and (h) of 

this AD, if the actions were performed before 

the effective date of this AD using Boeing 

Alert Service Bulletin 737–53A1214, 

Revision 4, dated December 16, 2011, which 

is not incorporated by reference in this AD. 

(l) 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 (m)(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 airplane, and the 

approval must specifically refer to this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–917–6450; fax: 425–917– 

6590; email: Alan.Pohl@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 20, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–30217 Filed 11–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2015–4006; Airspace 

Docket No. 15–ANE–3] 

Proposed Amendment of Class E 

Airspace; West Dover, VT 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

amend Class E Airspace at West Dover, 

VT as the Mt. Snow Non-Directional 

Beacon (NDB) has been 

decommissioned, requiring airspace 

redesign at Deerfield Valley Regional 

Airport. This action would enhance the 

safety and management of Instrument 

Flight Rules (IFR) operations at the 

airport. This action also would 

recognize the airport’s name change. 

DATES: Comments must be received on 

or before January 14, 2016. 

ADDRESSES: Send comments on this rule 

to: U. S. Department of Transportation, 

Docket Operations, 1200 New Jersey 

Avenue SE, West Bldg Ground Floor Rm 

W12–140, Washington, DC 20590–0001; 

Telephone: 1–800–647–5527; Fax: 202– 

493–2251. You must identify the Docket 

Number FAA–2015–4006; Airspace 

Docket No. 15–ANE–3, at the beginning 

of your comments. You may also submit 

and review received comments through 

the Internet at http://

www.regulations.gov. You may review 

the public docket containing the 

proposal, any comments received, and 

any final disposition in person in the 

Dockets Office between 9:00 a.m. and 

5:00 p.m., Monday through Friday, 

except Federal holidays. The Docket 

Office (telephone 1–800–647–5527), is 

on the ground floor of the building at 

the above address. 

FAA Order 7400.9Z, Airspace 

Designations and Reporting Points, and 

subsequent amendments can be viewed 

online at http://www.faa.gov/air_traffic/ 

publications/. For further information, 

you can contact the Airspace Policy and 

Regulations Group, Federal Aviation 

Administration, 800 Independence 

Avenue SW, Washington, DC, 20591; 

telephone: 202–267–8783. The Order is 

also available for inspection at the 

National Archives and Records 

Administration (NARA). For 

information on the availability of FAA 

Order 7400.9Z at NARA, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federalregulations/ibr_locations.html. 


jstallworth on DSK7TPTVN1PROD with PROPOSALS