Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations 24207 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on March 

25, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–07802 Filed 4–29–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0589; Directorate 

Identifier 2014–NM–069–AD; Amendment 

39–18148; AD 2015–09–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A318–111 and –112 

airplanes and Model A319, A320, and 

A321 series airplanes. This AD was 

prompted by reports of cracks on the 

forward corner fittings of engine pylon 

aft secondary structures. This AD 

requires repetitive inspections of certain 

forward corner fittings of the pylon aft 

secondary structures, and corrective 

actions if necessary. This AD also 

provides optional terminating action for 

the repetitive inspections. We are 

issuing this AD to detect and correct 

detachment of the lower fairing 

attachment and/or loss of the aft fixed 

fairing with the movable fairing from 

the airplane in flight, which could result 

in damage to the airplane. 

DATES: This AD becomes effective June 

4, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 4, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0589 or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this AD, 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. 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–2014–0589. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Airbus Model A318– 

111 and –112 airplanes and Model 

A319, A320, and A321 series airplanes. 

The NPRM published in the Federal 

Register on September 3, 2014 (79 FR 

52267). The NPRM was prompted by 

reports of cracks on the forward corner 

fittings of engine pylon aft secondary 

structures. The NPRM proposed to 

require repetitive inspections of certain 

forward corner fittings of the pylon aft 

secondary structures, and corrective 

actions if necessary. The NPRM also 

proposed to provide optional 

terminating action for the repetitive 

inspections. We are issuing this AD to 

detect and correct detachment of the 

lower fairing attachment and/or loss of 

the aft fixed fairing with the movable 

fairing from the airplane in flight, which 

could result in damage to the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0064, dated March 14, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition. The MCAI states: 

Several operators of A320 family 

aeroplanes have reported finding cracks on 

the forward corner fittings of engine pylon aft 

secondary structures, on the lateral face 

(lateral panel side). In some cases, these 

cracks had propagated onto the forward face 

(Rib 11 side). Investigation results have 

highlighted that these cracks are initiated by 

stress corrosion. 

This condition, if not detected and 

corrected, could lead to loss (i.e. detachment 

from the aeroplane) of the lower fairing 

attachment at Rib 10, and/or loss of the aft 

fixed fairing with the movable fairing, 

possibly resulting in * * * [damage to the 

airplane]. 

For the reasons described above, this 

[EASA] AD requires repetitive detailed 

inspections (DI) of the right hand (RH) Part 

Number (P/N) D54530014201 and left hand 

(LH) P/N D54530014200 corner fittings of 

engine pylon aft secondary structures (premod 38067 or pre-Airbus Service Bulletin 

(SB) A320–54–1019) to detect cracks or 

deformation in the splicing area with corner 

fitting between Ribs 11–12 and, depending 

on findings, replacement of the corner 

fittings. 

This [EASA] AD also recognizes that 

replacement of the corner fittings with 

improved parts (as per Airbus SB A320–54– 

1019) constitutes a terminating action for the 

repetitive DI required by this [EASA] AD. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0589- 

0003. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 52267, 

September 3, 2014) and the FAA’s 

response to each comment. 

Requests to Reference Revised Service 

Bulletins 

United Airlines and US Airways 

requested that we revise the NPRM (79 

FR 52267, September 3, 2014) to 

reference Airbus Service Bulletin A320– 

54–1019, Revision 02, dated April 15, 

2014, in lieu of Airbus Service Bulletin 

A320–54–1019, Revision 01, dated April 

10, 2008. United Airlines also requested 

that we revise the NPRM to reference 

Airbus Service Bulletin A320–54–1022, 

Revision 03, dated April 15, 2014, in 

lieu of Airbus Service Bulletin A320– 

54–1022, Revision 02, dated July 12, 

2013. 

We agree with the commenters’ 

requests to reference revised service 

bulletins. Airbus Service Bulletin A320– 

54–1019, Revision 02, dated April 15, 

2014, improves the test procedures, and 

Airbus Service Bulletin A320–54–1022, 

Revision 03, dated April 15, 2014, 

specifies that certain actions in the 

Accomplishment Instructions are 


rmajette on DSK2VPTVN1PROD with RULES
24208 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations 

required for compliance (RC). Both 

service bulletins state that no additional 

work is required for airplanes modified 

by any previous issue. We have revised 

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

reference Airbus Service Bulletin A320– 

54–1022, Revision 03, dated April 15, 

2014, and paragraphs (h)(2) and (i) of 

this AD to reference Airbus Service 

Bulletin A320–54–1019, Revision 02, 

dated April 15, 2014, as the appropriate 

sources of service information for 

accomplishing the required actions. 

We have redesignated paragraph (l) of 

the NPRM (79 FR 52267, September 3, 

2014) as paragraph (l)(1) of this AD and 

revised it to give credit for actions 

required by paragraphs (g) and (h) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Airbus Service Bulletin A320–54–1022, 

Revision 02, dated July 12, 2013. We 

have added new paragraph (l)(2) to this 

AD to give credit for actions required by 

paragraph (i) of this AD, if those actions 

were performed before the effective date 

of this AD using Airbus Service Bulletin 

A320–54–1019, Revision 01, dated April 

10, 2008. 

Airbus Service Bulletin A320–54– 

1022, Revision 03, dated April 15, 2014, 

steps that are identified as RC must be 

done to comply with the AD. However, 

steps that are not identified as RC are 

recommended. We have added an 

explanation of RC steps in the preamble 

of this AD. We have also added new 

paragraph (m)(3) to this AD to specify 

compliance with RC steps. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

52267, September 3, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 52267, 

September 3, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Explanation of ‘‘RC’’ Steps in Service 

Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directives 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. 

Procedures and tests that are 

identified as RC in any service 

information must be done to comply 

with the 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. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Airbus Service Bulletin 

A320–54–1022, Revision 03, dated April 

15, 2014. This service information 

describes procedures for inspections of 

forward corner fittings of the engine 

pylon aft secondary structures, and 

corrective actions. 

We also reviewed Airbus Service 

Bulletin A320–54–1019, Revision 02, 

dated April 15, 2014. This service 

information describes procedures for 

replacement of the corner fittings on the 

engine pylons. 

This service information is reasonably 

available at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2014–0589. Or see ADDRESSES for 

other ways to access this service 

information. 

Costs of Compliance 

We estimate that this AD affects 851 

airplanes of U.S. registry. 

We also estimate that it would take 

about 30 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $2,170,050, or $2,550 per 

product. 

In addition, we estimate the optional 

terminating modification would take 

about 60 work-hours and require parts 

costing about $932 per product, for a 

cost of $6,032 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. 

According to the manufacturer, some 

of the costs of this 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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

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 that this AD: 

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. 


rmajette on DSK2VPTVN1PROD with RULES
Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations 24209 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0589; 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 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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): 

2015–09–03 Airbus: Amendment 39–18148. 

Docket No. FAA–2014–0589; Directorate 

Identifier 2014–NM–069–AD. 

(a) Effective Date 

This AD becomes effective June 4, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1) through (c)(4) 

of this AD, certificated in any category, 

except for airplanes on which Airbus 

Modification 33844 or Modification 33847, as 

applicable, has been embodied in 

production. 

(1) Airbus Model A318–111 and –112 

airplanes. 

(2) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes. 

(3) Airbus Model A320–211, –212, –214, 

–231, –232, and –233 airplanes. 

(4) Airbus Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/pylons. 

(e) Reason 

This AD was prompted by reports of cracks 

on the forward corner fittings of engine pylon 

aft secondary structures. We are issuing this 

AD to detect and correct detachment of the 

lower fairing attachment and/or loss of the aft 

fixed fairing with the movable fairing from 

the airplane in flight, which could result in 

damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

At the latest of the times specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD: 

Do a detailed inspection for cracking of 

forward corner fittings having part number 

(P/N) D54530014201 (right-hand (RH)) and 

P/N D54530014200 (left-hand (LH)) of the 

pylon aft secondary structures, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–54–1022, 

Revision 03, dated April 15, 2014, except as 

provided by paragraph (j) of this AD. Repeat 

the inspection thereafter at intervals not to 

exceed 15,000 flight cycles or 22,500 flight 

hours, whichever occurs first. 

Accomplishment of the actions specified in 

paragraph (i) of this AD terminates the 

actions required by this paragraph. 

(1) Within 15,000 flight cycles or 22,500 

flight hours, whichever occurs first since first 

flight of the airplane. 

(2) Within 5,000 flight cycles or 7,500 

flight hours after the effective date of this AD, 

without exceeding 40,750 flight cycles or 

60,750 flight hours, whichever occurs first 

since first flight of the airplane. 

(3) Within 750 flight cycles or 750 flight 

hours, whichever occurs first after the 

effective date of this AD. 

(h) Related Investigative and Corrective 

Actions 

If any crack is found on the corner fittings 

of a pylon during any inspection required by 

paragraph (g) of this AD: Before further flight, 

do a detailed inspection for cracking of the 

lower and medium spars, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–54–1022, Revision 03, 

dated April 15, 2014. 

(1) If any damage is found: Before further 

flight, repair 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). 

(2) If no damage is found: Within 5,000 

flight cycles or 7,500 flight hours, whichever 

occurs first after the detailed inspection 

specified in the introductory text to 

paragraph (h) of this AD, modify the airplane, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

54–1019, Revision 02, dated April 15, 2014. 

(i) Optional Terminating Action 

Modification of an airplane by installation 

of corner fittings having P/N 

D0041092120000 (RH) and P/N 

D0041092120100 (LH) on both pylons, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

54–1019, Revision 02, dated April 15, 2014, 

constitutes terminating action for the 

repetitive inspections required by paragraph 

(g) of this AD. 

(j) Parts Installation Limitation 

Airplanes on which Airbus Modification 

38067 (installation of new corner fittings) has 

been embodied in production, and airplanes 

already modified in service as described in 

Airbus Service Bulletin A320–54–1019, are 

not affected by the requirements of paragraph 

(g) of this AD, provided that no corner 

fittings having P/N D54530014201 (RH) or P/ 

N D54530014200 (LH) have been installed 

since first flight of the airplane, or since 

modification, as applicable. 

(k) Parts Installation Prohibition 

(1) As of the effective date of this AD, for 

airplanes on which Airbus Modification 

38067 has been embodied in production on 

both pylons, and for airplanes previously 

modified in service as described in Airbus 

Service Bulletin A320–54–1019: Do not 

install any corner fittings having P/N 

D54530014201 (RH) or P/N D54530014200 

(LH). 

(2) After modification as required by 

paragraph (h) of this AD, or after optional 

modification as specified in paragraph (i) of 

this AD, as applicable: Do not install any 

corner fittings having P/N D54530014201 

(RH) or P/N D54530014200 (LH). 

(l) Credit for Previous Actions 

(1) This paragraph provides credit for 

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

this AD, if those actions were performed 

before the effective date of this AD using a 

service bulletin identified in paragraph 

(l)(1)(i), (l)(1)(ii), or (l)(1)(iii) of this AD; this 

service information is not incorporated by 

reference in this AD. 

(i) Airbus Service Bulletin A320–54–1022, 

dated July 7, 2009. 

(ii) Airbus Service Bulletin A320–54–1022, 

Revision 01, dated September 29, 2011. 

(iii) Airbus Service Bulletin A320–54– 

1022, Revision 02, dated July 12, 2013. 

(2) This paragraph provides credit for 

actions required by paragraphs (h)(2) and (i) 

of this AD, if those actions were performed 

before the effective date of this AD using 

Airbus Service Bulletin A320–54–1019, 

Revision 01, dated April 10, 2008, 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: 

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 


rmajette on DSK2VPTVN1PROD with RULES
24210 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations 

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 Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(3) Required for Compliance: Except as 

required by paragraph (i) of this AD: 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. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information EASA 

Airworthiness Directive 2014–0064, dated 

March 14, 2014, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0589-0003. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (o)(3) and (o)(4) of this AD. 

(o) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A320–54–1019, 

Revision 02, dated April 15, 2014. 

(ii) Airbus Service Bulletin A320–54–1022, 

Revision 03, dated April 15, 2014. 

(3) For service information identified in 

this AD, 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. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on April 17, 

2015. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–09811 Filed 4–29–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE INTERIOR 

National Park Service 

36 CFR Part 7 

[NPS–BRCA–17884; PA.PD191235A.00.3] 

RIN 1024–AE23 

Special Regulations, Areas of the 

National Park System, Bryce Canyon 

National Park, Bicycling 

AGENCY: National Park Service, Interior. 

ACTION: Final rule. 

SUMMARY: The National Park Service is 

planning to construct a paved, multi-use 

visitor path in Bryce Canyon National 

Park. The path will be approximately 

6.2 miles long and be open to several 

uses, including running, walking, and 

bicycling. National Park Service 

regulations require promulgation of a 

special regulation to designate new 

routes for bicycle use off park roads and 

outside developed areas. 

DATES: This rule is effective June 1, 

2015. 

FOR FURTHER INFORMATION CONTACT: 

Daniel J. Cloud, Chief of Facility 

Management, Bryce Canyon National 

Park, P.O. Box 640201, Bryce Canyon, 

UT 84764–0201. Phone: (435) 834–4720. 

Email: daniel_cloud@nps.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

Bryce Canyon National Park (BRCA or 

park) is in south-central Utah. The park 

encompasses approximately 35,835 

acres and ranges between 6,600 and 

9,100 feet in elevation. BRCA was 

originally established as a national 

monument by presidential proclamation 

in 1923. The park was renamed Utah 

National Park in 1924, and the name 

was changed to Bryce Canyon National 

Park in 1928. 

The park’s most noted feature is the 

eroded landscape below the east rim of 

the Paunsaugunt Plateau. The erosional 

force of frost-wedging and the 

dissolving power of rainwater have 

worn away the colorful and weak 

limestone rock into bizarre shapes, 

including slot canyons, windows, fins, 

and spires called ‘‘hoodoos.’’ Because 

the park transcends 2,500 feet of 

elevation, the park exists in three 

distinct climatic zones characterized by 

spruce/fir forest, ponderosa pine forest, 

and pinyon pine/juniper woodlands. 

The diversity of forest and meadow 

habitats provides a high degree of plant 

and animal diversity. BRCA is also one 

of the best places to experience a truly 

dark night sky. 

The park’s purpose statement, which 

provides the foundation for park 

management, administration, and use 

decisions, states that ‘‘Bryce Canyon 

National Park protects and conserves 

resources integral to a landscape of 

unusual scenic beauty exemplified by 

highly colored and fantastically eroded 

geological features, including rock fins 

and spires, for the benefit and 

enjoyment of the people.’’ (May 2014 

Foundation Document). The park’s 

Foundation Document identifies 

‘‘increased use of alternative 

transportation (e.g., biking, hiking) 

within and surrounding the park’’ as an 

opportunity to protect clean air—one of 

the fundamental resources of the park. 

The proposal to construct a multi-use 

path in the park will support the park’s 

purpose statement by providing a new 

opportunity for safe enjoyment and 

protection of the fundamental resources 

in the park. 

Purpose of the Multi-Use Path 

The primary purpose of the multi-use 

path is to relieve safety problems for 

visitors of all ages who choose to use 

non-motorized transportation to 

experience the park and adjacent United 

States Forest Service (USFS) areas near 

Bryce Canyon City. Increases in 

visitation of the park (30% increase 

between 2008 and 2012) are leading to 

transportation system capacity problems 

and traffic congestion. Cyclists and 

pedestrians need a way to travel to and 

within the park that is safer, provides a 

better visitor experience, and promotes 

non-motorized travel between nearby 

communities and the park as well as 

between key destinations in the park. 

The path will enhance the park’s 

transportation system by connecting the 

park’s gateway communities with high 

visitor use areas along the canyon rim 

in the Bryce Amphitheater and with 

other key features of the park. The 

proposed path will also connect to the 

existing transportation system, 

including visitor shuttle buses, hiking 

trails and walking paths, parking lots, 

and roads. This will link major visitor 

attractions and facilities with both nonmotorized and motorized transportation 

modes. Visitor safety will be improved 


rmajette on DSK2VPTVN1PROD with RULES