Federal Register / Vol. 79, No. 229 / Friday, November 28, 2014 / Rules and Regulations 70787 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2014–07–51, Amendment 39–17902 (79 

FR 45329, August 5, 2014), and adding 

the following new AD: 

2014–24–02 Agusta S.p.A. (Agusta): 

Amendment 39–18035; Docket No. FAA– 

2014–0971; Directorate Identifier 2014–SW– 

055–AD. 

(a) Applicability 

This AD applies to Agusta Model AB139 

and AW139 helicopters with main rotor (M/ 

R) rotating scissors part number (P/N) 

3G6230A00733, with a lower half scissors 

spherical bearing (bearing) P/N 

3G6230V00654 installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

excessive play of the bearing in the M/R 

rotating scissors. This condition could result 

in failure of the M/R rotating scissors and 

subsequent loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2014–07–51, 

Amendment 39–17902 (79 FR 45329, August 

5, 2014). 

(d) Effective Date 

This AD becomes effective December 15, 

2014. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

(1) For helicopters with the M/R rotating 

controls installed without special nut P/N 

3G6230A06851, within 5 hours time-inservice (TIS), and thereafter before the first 

flight of each day or at intervals not 

exceeding 24 hours, whichever occurs later; 

and for helicopters with the M/R rotating 

controls installed with special nut P/N 

3G6230A06851, within 25 hours TIS, and 

thereafter at intervals not exceeding 25 hours 

TIS: 

(i) Visually inspect the M/R rotating 

scissors for damage using a light source and 

a magnifying glass, paying particular 

attention to the bearings. Some examples of 

damage are shown in Figures 4 through 8 of 

AgustaWestland Bollettino Tecnico No. 139– 

392, dated September 23, 2014 (BT 139–392). 

If there is damage, before further flight, 

remove the bearing. 

(ii) Inspect the M/R rotating scissors for 

play of each bearing, paying particular 

attention to the bearing staking condition, by 

manually moving the lower half scissor along 

the axis of the spherical bearing. Refer to 

Figure 1 of BT 139–392. If there is play, 

before further flight, accomplish a detailed 

inspection of the M/R rotating scissors in 

accordance with steps 9.1 through 12.9 of 

AgustaWestland AW139 Document Code 39– 

C–62–31–00–00A–286C–A, Rotating control 

installation—Fixed swashplate and rotating 

scissors—Detailed inspection, issue 001, 

dated August 6, 2012. Any play beyond 

allowable limits requires removing the 

bearing before further flight. 

(2) Within 50 hours TIS from August 20, 

2014, remove any bearing from a M/R 

rotating scissors with serial numbers (S/N) 

listed in Table 1 of AgustaWestland Bolletino 

Tecnico No. 139–368, dated March 19, 2014 

(BT 139–368), on which the bearing has 

never been replaced; or from a M/R rotating 

scissors on which the bearing was replaced 

with a bearing with a S/N listed in Table 2 

of BT 139–368. 

(3) Within 100 hours TIS, install special 

nut P/N 3G6230A06851 in accordance with 

steps 5.1. through 6., Part II, of the 

Compliance Instructions, of BT 139–392. 

(4) Prior to installing a M/R rotating 

scissors with a S/N listed in Table 1 of BT 

139–368, replace the bearing and re-identify 

the M/R rotating scissors in accordance with 

paragraphs 4.2 through 4.4., Part II, of the 

Compliance Instructions of BT 139–368. 

(5) Do not install a bearing with a S/N 

listed in Table 2 of BT 139–368 into any M/ 

R rotating scissors. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, FAA, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone (817) 222– 

5110; email robert.grant@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) 

Emergency AD 2014–0215–E, dated 

September 24, 2014. You may view the EASA 

AD on the Internet at http://

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2014–0971. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6200, M/R System. 

(j) 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 the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on December 15, 2014. 

(i) AgustaWestland Bollettino Tecnico No. 

139–392, dated September 23, 2014. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on August 20, 2014 (79 FR 

45329, August 5, 2014). 

(i) AgustaWestland Bollettino Tecnico No. 

139–368, dated March 19, 2014. 

(ii) AgustaWestland AW139 Document 

Code 39–C–62–31–00–00A–286C–A, Rotating 

control installation—Fixed swashplate and 

rotating scissors—Detailed inspection, issue 

001, dated August 6, 2012. 

(5) For AgustaWestland, Product Support 

Engineering, Via del Gregge, 100, 21015 

Lonate Pozzolo (VA) Italy, ATTN: Maurizio 

D’Angelo; telephone 39 0331–664757; fax 39 

0331–664680; or at http://

www.agustawestland.com/technicalbulletins. 

(6) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(7) 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 Fort Worth, Texas, on November 

17, 2014. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–27995 Filed 11–26–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0235; Directorate 

Identifier 2013–NM–249–AD; Amendment 

39–18015; AD 2014–22–10] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model DC–8–55, 

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. This AD was 

prompted by multiple reports of 

cracking of the upper aft skin panel of 


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70788 Federal Register / Vol. 79, No. 229 / Friday, November 28, 2014 / Rules and Regulations 

the fuselage. An evaluation by the 

design approval holder (DAH) indicates 

that the upper aft skin panel of the 

fuselage is subject to widespread fatigue 

damage (WFD). This AD requires 

removing any previously installed local 

repairs; installing a full-length 

improvement modification with or 

without finger doublers, or a full-length 

repair with or without finger doublers, 

as applicable; and doing repetitive 

inspections for cracking of the doublers, 

and repair if necessary. We are issuing 

this AD to detect and correct fatigue 

cracking of the upper aft skin panel of 

the fuselage, which could result in loss 

of structural integrity and consequent 

rapid decompression of the airplane. 

DATES: This AD is effective January 2, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 2, 2015. 

ADDRESSES: For service information 

identified in this 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. 

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–2014– 

0235; 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 address for the 

Docket Office (phone: 800–647–5527) is 

Document 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 20590. 

FOR FURTHER INFORMATION CONTACT: 

Chandraduth Ramdoss, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles Aircraft Certification 

Office (ACO), 3960 Paramount Blvd., 

Suite 100, Lakewood, CA 90712–4137, 

phone: 562–627–5239; fax: 562–627– 

5210; email: 

chandraduth.ramdoss@faa.gov. 

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 The Boeing Company 

Model DC–8–55, 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. The NPRM published in the 

Federal Register on April 17, 2014 (79 

FR 21648). The NPRM was prompted by 

multiple reports of cracking of the upper 

aft skin panel of the fuselage. An 

evaluation by the DAH indicates that 

the upper aft skin panel of the fuselage 

is subject to WFD. The NPRM proposed 

to require removing any previously 

installed local repairs; installing a fulllength improvement modification with 

finger doublers or a full-length repair 

with finger doublers; and doing 

repetitive inspections for cracking of the 

doublers, and repair if necessary. We are 

issuing this AD to detect and correct 

fatigue cracking of the upper aft skin 

panel of the fuselage, which could result 

in loss of structural integrity and 

consequent rapid decompression of the 

airplane. 

Comment 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (79 FR 21648, 

April 17, 2014), and the FAA’s response 

to the comment. 

Request To Revise Repair or 

Modification Procedure 

Boeing requested that we revise 

paragraph (g) of the NPRM (79 FR 

21648, April 17, 2014) to allow 

operators the option to repair or modify 

without finger doublers. Boeing also 

requested that we revise the inspection 

requirements of paragraph (h) of the 

NPRM to address the option to repair or 

modify without finger doublers. Boeing 

stated that the service rework drawing 

that is referenced in Boeing Alert 

Service Bulletin DC8–53A080, Revision 

2, dated September 18, 2013, includes 

two repair and preventive modification 

configurations, depending on whether 

finger doublers will be installed. 

We agree with the commenter’s 

request to allow the procedure to repair 

or modify without finger doublers as an 

approved option for repair or 

modification. We have revised 

paragraphs (g) and (h)(1) of this final 

rule accordingly. 

Conclusion 

We reviewed the relevant data, 

considered the comment 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 

21648, April 17, 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 21648, 

April 17, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 18 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on 

U.S. operators 

Full-length modification or repair ............................................ Up to 184 work-hours × $85 

per hour = $15,640.

Up to $14,720 Up to $30,360 Up to 

$546,480. 

Inspection ............................................................................... 9 work-hours × $85 per hour 

= $765 per inspection cycle.

$0 ................... $765 per inspection 

cycle.

$13,770 per 

inspection 

cycle. 


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Federal Register / Vol. 79, No. 229 / Friday, November 28, 2014 / Rules and Regulations 70789 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

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 

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. 

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): 

2014–22–10 The Boeing Company: 

Amendment 39–18015; Docket No. 

FAA–2014–0235; Directorate Identifier 

2013–MN–249–AD. 

(a) Effective Date 

This AD is effective January 2, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

airplanes identified in paragraphs (c)(1) 

through (c)(6) of this AD, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin DC8–53A080, Revision 2, 

dated September 18, 2013. 

(1) The Boeing Company Model DC–8–55 

airplanes. 

(2) The Boeing Company Model DC–8F–54 

and DC–8F–55 airplanes. 

(3) The Boeing Company Model DC–8–61, 

DC–8–62, and DC–8–63 airplanes. 

(4) The Boeing Company Model DC–8–61F, 

DC–8–62F, and DC–8–63F airplanes. 

(5) The Boeing Company Model DC–8–71, 

DC–8–72, and DC–8–73 airplanes. 

(6) The Boeing Company Model DC–8–71F, 

DC–8–72F, and DC–8–73F airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by multiple reports 

of cracking of the upper aft skin panel of the 

fuselage. An evaluation by the design 

approval holder indicates that the upper aft 

skin panel of the fuselage is subject to 

widespread fatigue damage. We are issuing 

this AD to detect and correct fatigue cracking 

of the upper aft skin panel of the fuselage, 

which could result in loss of structural 

integrity and consequent rapid 

decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification or Repair 

Before the accumulation of 45,400 total 

flight cycles, or within 72 months after the 

effective date of this AD, whichever occurs 

later: Remove any previously installed local 

repairs and install a full-length improvement 

modification with or without finger doublers, 

or a full-length repair with or without finger 

doublers, as applicable, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin DC8–53A080, Revision 

2, dated September 18, 2013. Installation of 

the full-length improvement modification or 

full-length repair, in accordance with 

paragraph (i) of AD 2008–06–23, Amendment 

39–15435 (73 FR 14378, March 18, 2008), is 

a method of compliance with the 

requirements of this paragraph. Installation 

of a local repair as specified in paragraph (i) 

of AD 2008–06–23, does not comply with the 

requirements of this paragraph. 

(h) Post-Modification or Post-Repair 

Repetitive Inspections 

After accomplishing the actions required 

by paragraph (g) of this AD, at the applicable 

time and intervals specified in paragraph 

(h)(1) or (h)(2) of this AD: Do an external 

visual inspection or low frequency eddy 

current (LFEC) inspection for cracking along 

all four edges of each external doubler, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

DC8–53A080, Revision 2, dated September 

18, 2013. Repeat the inspections thereafter at 

the applicable time and interval specified in 

paragraphs (h)(1) and (h)(2) of this AD. 

Accomplishment of the applicable repetitive 

inspection specified in paragraph (j)(1) or 

(j)(2)(ii) of AD 2008–06–23, Amendment 39– 

15435 (73 FR 14378, March 18, 2008), is a 

method of compliance with the applicable 

inspection requirements of this paragraph. 

(1) For repair or modification with finger 

doublers: Within 30,000 flight cycles after 

doing the actions specified in paragraph (g) 

of this AD, do an external visual inspection. 

Repeat the external visual inspection 

thereafter at intervals not to exceed 5,000 

flight cycles. 

(2) For repair or modification without 

finger doublers: Within 15,000 flight cycles 

after doing the actions specified in paragraph 

(g) of this AD, do a LFEC inspection. Repeat 

the LFEC inspection thereafter at intervals 

not to exceed 10,000 flight cycles. 

(i) Cracking Repair 

If any cracking is found during any 

inspection required by paragraph (h) of this 

AD: Before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (k) of this 

AD. 

(j) Credit for Previous Actions 

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 Boeing Alert 

Service Bulletin DC8–53A080, dated June 22, 

2004; or Boeing Alert Service Bulletin DC8– 

53A080, Revision 1, dated May 3, 2013. 

Boeing Alert Service Bulletin DC8–53A080, 

dated June 22, 2004, is incorporated by 

reference in AD 2008–06–23, Amendment 

39–15435 (73 FR 14378, March 18, 2008). 

Boeing Alert Service Bulletin DC8–53A080, 

Revision 1, dated May 3, 2013, is not 

incorporated by reference in this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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, 


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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 (l)(1) of this AD. Information may 

be emailed to: 9–ANM–LAACO–AMOC– 

REQUESTS@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, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

(l) Related Information 

(1) For more information about this AD, 

contact Chandraduth Ramdoss, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles Aircraft Certification 

Office (ACO), 3960 Paramount Blvd., Suite 

100, Lakewood, CA 90712–4137, phone: 562– 

627–5239; fax: 562–627–5210; email: 

chandraduth.ramdoss@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (m)(3) and (m)(4) of this AD 

(m) 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 the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin DC8– 

53A080, Revision 2, dated September 18, 

2013. 

(ii) Reserved. 

(3) For Boeing service information 

identified in this 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. 

(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 October 

28, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–26439 Filed 11–26–14; 8:45 am] 

BILLING CODE 4910–13–P 

FEDERAL COMMUNICATIONS 

COMMISSION 

47 CFR Parts 1 and 20 

[WT Docket No. 10–4; FCC 14–138] 

The Commission’s Rules To Improve 

Wireless Coverage Through the Use of 

Signal Boosters 

AGENCY: Federal Communications 

Commission. 

ACTION: Final rule; petition for 

reconsideration. 

SUMMARY: In the Order on 

Reconsideration, the Commission 

addresses two Petitions for 

Reconsideration of the technical rules 

adopted in the Signal Boosters Report 

and Order, granting one petition and 

granting the other in part. 

DATES: Effective December 29, 2014, 

except for the revision to 47 CFR 

20.21(f)(1)(iv)(A)(2), which contains 

information collection requirements 

subject to the Paperwork Reduction Act 

of 1995, Public Law 104–13, that are not 

effective until after approval by the 

Office of Management and Budget. The 

Federal Communications Commission 

will publish a document in the Federal 

Register announcing OMB approval and 

the effective date of this rule revision. 

FOR FURTHER INFORMATION CONTACT: 

Amanda Huetinck of the Mobility 

Division, Wireless Telecommunications 

Bureau, at (202) 418–7090 or 

Amanda.Huetinck@fcc.gov. For 

additional information concerning the 

Paperwork Reduction Act information 

collection requirements contained in 

this document, contact Cathy Williams 

at (202) 418–2918, or via the Internet at 

PRA@fcc.gov. 

SUPPLEMENTARY INFORMATION: This is the 

Federal Communications Commission’s 

Order on Reconsideration, in WT 

Docket No. 10–4, FCC 14–138, adopted 

September 19, 2014, and released 

September 23, 2014. The Further Notice 

of Proposed Rulemaking that was 

adopted concurrently with the Order on 

Reconsideration is published elsewhere 

in this issue of the Federal Register. 

The full text of that document is 

available for inspection and copying 

during normal business hours in the 

FCC Reference Center, 445 12th Street 

SW., Room CY–A257, Washington, DC 

20554, or by downloading the text from 

the Commission’s Web site at http://

www.fcc.gov/document/signal-boostersorder-reconsideration-and-fnprm. The 

complete text also may be purchased 

from the Commission’s duplicating 

contractor, Best Copy and Printing, Inc., 

Portals II, 445 12th Street SW., Suite 

CY–B402, Washington, DC 20554. 

Alternative formats are available for 

people with disabilities (Braille, large 

print, electronic files, audio format), by 

sending an email to FCC504@fcc.gov or 

calling the Consumer and Government 

Affairs Bureau at (202) 418–0530 

(voice), (202) 418–0432 (TTY). 

Synopsis 

I. Introduction and Background 

1. In the Order on Reconsideration, 

we address two Petitions for 

Reconsideration of the technical rules 

adopted in the Signal Boosters Report 

and Order. 

2. As discussed below, we grant the 

Wi-Ex Petition and amend certain 

technical rules for Wideband Consumer 

Signal Boosters. These amendments will 

streamline the testing procedures for 

Wideband Consumer Signal Boosters 

and will benefit consumers by 

decreasing the costs and complexities 

associated with the manufacture and 

certification of such devices. We also 

grant in part, to the extent described 

below, and otherwise deny the Verizon 

Petition and amend certain technical 

rules for mobile Provider-Specific 

Consumer Signal Boosters. These 

amendments will ensure consumers 

have access to a wide variety of signal 

boosters while strengthening the 

technical protections for wireless 

networks. 

II. Order on Reconsideration 

A. Background 

3. Report and Order. On February 20, 

2013, the Commission adopted a new 

regulatory framework to allow 

consumers to realize the benefits of 

using signal boosters while preventing, 

controlling, and, if necessary, resolving 

interference to wireless networks. In the 

Report and Order, the Commission 

adopted new technical, operational, and 

registration requirements for signal 

boosters. The new rules created two 

classes of signal boosters—Consumer 

and Industrial—with distinct regulatory 

requirements for each. For Consumer 

Signal Boosters, the Commission 

adopted a Network Protection Standard 

(NPS)—a flexible set of requirements for 

the design and manufacture of 

Consumer Signal Boosters, which are 

intended to couple signal booster 


tkelley on DSK3SPTVN1PROD with RULES