This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

27001 

Vol. 78, No. 90 

Thursday, May 9, 2013 

DEPARTMENT OF AGRICULTURE 

Animal and Plant Health Inspection 

Service 

9 CFR Part 11 

[Docket No. APHIS–2011–0030] 

RIN 0579–AD43 

Horse Protection Act; Requiring Horse 

Industry Organizations To Assess and 

Enforce Minimum Penalties for 

Violations; Correction 

AGENCY: Animal and Plant Health 

Inspection Service, USDA. 

ACTION: Correcting amendment. 

SUMMARY: In a final rule that was 

published in the Federal Register on 

June 7, 2012, and effective on July 9, 

2012, we amended the horse protection 

regulations to require horse industry 

organizations or associations that 

license Designated Qualified Persons to 

assess and enforce minimum penalties 

for violations of the Horse Protection 

Act. This document corrects an error in 

that final rule. 

DATES: Effective May 9, 2013. 

FOR FURTHER INFORMATION CONTACT: Dr. 

Rachel Cezar, Horse Protection National 

Coordinator, Animal Care, APHIS, 4700 

River Road, Unit 84, Riverdale, MD 

20737; (301) 851–3746. 

SUPPLEMENTARY INFORMATION: 

Background 

In a final rule that was published in 

the Federal Register on June 7, 2012 (77 

FR 33607–33619, Docket No. APHIS– 

2011–0030), and effective on July 9, 

2012, we amended the horse protection 

regulations in 9 CFR part 11 to require 

horse industry organizations or 

associations that license Designated 

Qualified Persons to assess and enforce 

minimum penalties for violations of the 

Horse Protection Act. We established 

the minimum penalties in a new 

§ 11.25. 

As part of this change, we amended 

paragraph (d) of § 11.21 to indicate that 

horse industry organizations or 

associations are required to assess and 

enforce penalties for violations in 

accordance with § 11.25. Before the 

publication of the June 2012 final rule, 

this paragraph also indicated that horse 

industry organizations or associations 

had to report all violations in 

accordance with § 11.20(b)(3). However, 

in revising § 11.21(d) to reflect the new 

minimum penalty requirements, we 

erroneously changed the paragraph 

reference in the existing reporting 

requirement to § 11.20(b)(4), which does 

not exist. This document corrects that 

error. 

List of Subjects in 9 CFR Part 11 

Animal welfare, Horses, Reporting 

and recordkeeping requirements. 

Accordingly, 9 CFR part 11 is 

corrected by making the following 

correcting amendment: 

PART 11—HORSE PROTECTION 

REGULATIONS 

■ 1. The authority citation for part 11 

continues to read as follows: 

Authority: 15 U.S.C. 1823–1825 and 1828; 

7 CFR 2.22, 2.80, and 371.7. 

§ 11.21 [Amended] 

■ 2. In § 11.21, paragraph (d), the 

citation ‘‘§ 11.20(b)(4)’’ is removed and 

the citation ‘‘§ 11.20(b)(3)’’ is added in 

its place. 

Done in Washington, DC, this 3rd day of 

May 2013. 

Kevin Shea, 

Acting Administrator, Animal and Plant 

Health Inspection Service. 

[FR Doc. 2013–11028 Filed 5–8–13; 8:45 am] 

BILLING CODE 3410–34–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1161; Directorate 

Identifier 2011–NM–277–AD; Amendment 

39–17442; AD 2013–09–01] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain The Boeing Company Model 

737–200, –200C, –300, –400, and –500 

series airplanes. That AD currently 

requires a one-time mid-frequency eddy 

current (MFEC) inspection, a lowfrequency eddy current (LFEC) 

inspection, and a detailed inspection for 

damage or cracking of stringer S–4L and 

S–4R lap joints and stringer clips 

between body station (BS) 540 and BS 

727, and follow-on inspections and 

repair if necessary. This new AD instead 

requires repetitive external eddy current 

inspections for cracking of certain 

fuselage crown lap joints, and corrective 

actions if necessary; internal eddy 

current and detailed inspections for 

cracking of certain fuselage crown lap 

joints, and repair if necessary; and 

detailed inspections of certain stringer 

clips, and replacement with new 

stringer clips if necessary. This AD also 

adds airplanes to the applicability. This 

AD was prompted by reports of cracking 

of the lap joint lower row. We are 

issuing this AD to detect and correct 

cracking of the fuselage lap joints, 

which could result in sudden 

decompression of the airplane. 

DATES: This AD is effective June 13, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publication listed in the AD 

as of June 13, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of May 17, 2002 (67 FR 

17917, April 12, 2002). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 


tkelley on DSK3SPTVN1PROD with RULES
27002 Federal Register / Vol. 78, No. 90 / Thursday, May 9, 2013 / Rules and Regulations 

& 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 

review copies of the 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; 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: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6447; fax: 

425–917–6590; email: 

wayne.lockett@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2003–08–15, 

Amendment 39–13128 (68 FR 20341, 

April 25, 2003). That AD applies to the 

specified products. The NPRM 

published in the Federal Register on 

November 7, 2012 (77 FR 66757). That 

NPRM proposed to require repetitive 

external eddy current inspections for 

cracking of certain fuselage crown lap 

joints and corrective actions; internal 

eddy current and detailed inspections 

for cracking of certain fuselage crown 

lap joints, and repair if necessary; and 

detailed inspections of certain stringer 

clips, and replacement with new 

stringer clips if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (77 FR 66757, 

November 7, 2012) and the FAA’s 

response to each comment. 

Support of NPRM (77 FR 66757, 

November 7, 2012) 

Ann Harrison stated that she supports 

the NPRM (77 FR 66757, November 7, 

2012). 

Request for Clarification of Inspection 

Requirements 

Boeing and Lufthansa requested 

clarification that the repetitive 

inspections referred to in paragraph 

(i)(3) of the NPRM (77 FR 66757, 

November 7, 2012) are external 

inspections. The commenters noted that 

the internal inspection specified in 

Boeing Alert Service Bulletin 737– 

53A1255, Revision 2, dated August 7, 

2012, is a one-time inspection. 

Lufthansa suggested we delete 

paragraph (i)(3) from the NPRM. Boeing 

suggested we revise paragraph (i)(3) of 

the NPRM to state that the repetitive 

inspection is external. 

We agree that clarification is needed. 

The internal inspection is required only 

once prior to the accomplishment of the 

lap splice modification. Since the 

external inspection specified in 

paragraph (g) of this AD is repetitive, we 

have deleted paragraph (i)(3) of this AD. 

Request To Use Previous Alternative 

Methods of Compliance (AMOCs) 

Alaska Airlines requested that we 

change the NPRM (77 FR 66757, 

November 7, 2012) to state that 

‘‘AMOCs approved previously in 

accordance with AD 2003–08–15 [(68 

FR 20341, April 25, 2003)] and AD 

2004–18–06 [(69 FR 54206, September 

8, 2004)] are approved as AMOCs for the 

corresponding provisions of this AD.’’ 

Alaska Airlines stated that there is a 

global AMOC for the PEMCO main deck 

cargo door installation in accordance 

with supplemental type certificate (STC) 

SA2969SO (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/2A10F5D4090A5346

86257A79006F0F97?

OpenDocument&Highligh

t=stcsa2969so). The commenter stated 

that since the STC is not a repair, this 

global AMOC should be specified in 

paragraph (n) of the NPRM. 

We agree with the request to include 

in the AD previously approved AMOCs 

for the corresponding requirements of 

this AD. Installation of the PEMCO main 

deck cargo door done in accordance 

with STC SA2969SO (http://rgl.faa.gov/ 

Regulatory_and_Guidance_Library/

rgstc.nsf/0/2A10F5D4090A5346

86257A79006F0F97?OpenDocument&

Highlight=stcsa2969so) involves 

installation of an external doubler onto 

the existing skin and lap splices from 

stringer S–3R to S–23L between body 

station (BS) 312 and BS 500B. We have 

added new paragraph (n)(6) to this AD 

to state that installation of STC 

SA2969SO is approved as an AMOC to 

the corresponding requirements of 

paragraphs (g) and (i) of this AD from 

stringer S–3R to S–23L between BS 312 

and BS 500B only. 

Boeing requested that we revise 

paragraph (n)(4) of the NPRM (77 FR 

66757, November 7, 2012) to add 

references to paragraphs (g) and (h) of 

AD 2002–07–08, Amendment 39–12702 

(67 FR 17917, April 12, 2002), in order 

to provide approval for lap joint 

modifications that have been approved 

as AMOCs to paragraphs (g) and (h) of 

AD 2002–07–08. 

We agree with the request. Lap joints 

modified prior to the effective date of 

this AD that have been approved as an 

AMOC for paragraphs (g) and (h) of AD 

2002–07–08, Amendment 39–12702 (67 

FR 17917, April 12, 2002), should not be 

subject to the lap joint inspections 

required by this AD. We have added 

references to paragraphs (g) and (h) of 

AD 2002–07–08 to paragraph (n)(4) of 

this AD. 

STC Winglet Comment 

Aviation Partners Boeing stated that 

the installation of winglets per STC 

ST01219SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/2C6E3DBDDD36F91C8

62576A4005D64E2?OpenDocument&

Highlight=st01219se) does not affect the 

accomplishment of the manufacturer’s 

service instructions. 

We have added paragraph (c)(2) to 

this AD to state that installation of STC 

ST01219SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/2C6E3DBDDD36F

91C862576A4005D64E2?

OpenDocument&Highlight=st01219se) 

does not affect the ability to accomplish 

the actions required by this AD. 

Therefore, for airplanes on which STC 

ST01219SE is installed, a ‘‘change in 

product’’ AMOC approval request is not 

necessary to comply with the 

requirements of 14 CFR 39.17. For all 

other AMOC requests, the operator must 

request approval for an AMOC in 

accordance with the procedures 

specified in paragraph (n) of this AD. 

Request To Clarify Locations of 

Optional Internal Inspections 

Boeing requested that we include 

further clarification in paragraph (h) of 

the NPRM (77 FR 66757, November 7, 

2012) indicating that the optional 

internal inspections are for cracks 

between tear straps only. Boeing stated 

that paragraph (g) of the NPRM inspects 

for cracking at tear strap locations and 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 78, No. 90 / Thursday, May 9, 2013 / Rules and Regulations 27003 

between tear straps. Boeing also stated 

that paragraph (h) of the NPRM provides 

an optional inspection for the 

inspections required by paragraph (g), 

but only for cracking between tear 

straps. Boeing added that it is important 

to clarify that the inspections required 

by paragraph (h) of the NPRM are only 

applicable at locations between tear 

straps. 

We agree that the requested wording 

will further clarify the location for the 

optional internal inspections specified 

in paragraph (h) of this AD. We have 

added the phrase ‘‘between tear straps’’ 

to the beginning of the first sentence of 

paragraph (h) of this AD. 

Boeing also requested that we clarify 

paragraph (j) of the NPRM (77 FR 66757, 

November 7, 2012) to indicate that the 

optional internal inspections are for 

cracks at tear strap locations. Boeing 

added that the wording in the NPRM 

only allows this confirmation when 

accomplishing the internal inspections 

specified in paragraph (i) of the NPRM. 

Boeing stated that Boeing Alert Service 

Bulletin 737–53A1255, Revision 2, 

dated August 7, 2012, specifies that this 

optional inspection at tear strap 

locations is for cracks found during 

either the external inspection specified 

in paragraph (g) of the NPRM, or the 

internal inspections specified in 

paragraph (i) of the NPRM. 

We agree that adding a reference to 

the tear strap location near the 

beginning of the first sentence of 

paragraph (j) of this AD will clarify the 

requirement. We have revised paragraph 

(j) of this AD accordingly. We have also 

added a reference to paragraph (g) of 

this AD, as requested by the commenter. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the 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 (77 FR 

66757, November 7, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 66757, 

November 7, 2012). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD affects 307 

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 

Number of 

airplanes 

Cost on 

U.S. operators 

Internal inspection ......... Up to 303 work-hours × $85 per hour = $25,755 $0 $25,755 307 $7,906,785 

External inspection ........ Up to 10 work-hours × $85 per hour = $850 ...... 0 850 307 260,950 

We have received no definitive data 

that would enable us to provide a cost 

estimate 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 

We have 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 

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 

removing airworthiness directive (AD) 

2003–08–15, Amendment 39–13128 (68 

FR 20341, April 25, 2003), and adding 

the following new AD: 

2013–09–01 The Boeing Company: 

Amendment 39–17442; Docket No. 

FAA–2012–1161; Directorate Identifier 

2011–NM–277–AD. 

(a) Effective Date 

This AD is effective June 13, 2013. 

(b) Affected ADs 

This AD supersedes AD 2003–08–15, 

Amendment 39–13128 (68 FR 20341, April 

25, 2003). 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 737–200, –200C, –300, 

–400, and –500 series airplanes; certificated 

in any category; as specified in Boeing Alert 

Service Bulletin 737–53A1255, Revision 2, 

dated August 7, 2012. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE (http://rgl.faa.

gov/Regulatory_and_Guidance_Library/ 

rgstc.nsf/0/

2C6E3DBDDD36F91C862576A4005D64E2?

OpenDocument&Highlight=st01219se) does 

not affect the ability to accomplish the 

actions required by this AD. Therefore, for 

airplanes on which STC ST01219SE is 

installed, a ‘‘change in product’’ alternative 

method of compliance (AMOC) approval 


tkelley on DSK3SPTVN1PROD with RULES
27004 Federal Register / Vol. 78, No. 90 / Thursday, May 9, 2013 / Rules and Regulations 

request is not necessary to comply with the 

requirements of 14 CFR 39.17. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking of the lap joint lower row. We are 

issuing this AD to detect and correct cracking 

of the fuselage lap joints, which could result 

in sudden decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) External Crown Lap Joint Inspection and 

Repair 

For airplanes on which the lap splice 

modification specified in AD 2002–07–08, 

Amendment 39–12702 (67 FR 17917, April 

12, 2002), has not been accomplished, except 

as required by paragraphs (l)(1) and (l)(2) of 

this AD: At the applicable times specified in 

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

Alert Service Bulletin 737–53A1255, 

Revision 2, dated August 7, 2012, do an 

external eddy current inspection for cracking 

in the crown lap joints, except as provided 

by paragraphs (h) and (j) of this AD, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1255, Revision 2, dated August 7, 

2012. At the intervals specified in paragraph 

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

Bulletin 737–53A1255, Revision 2, dated 

August 7, 2012, repeat the inspections, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1255, Revision 2, dated August 7, 

2012. If any cracking is found in a lap joint, 

before further flight, repair, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1255, 

Revision 2, dated August 7, 2012. 

(h) Optional Internal Inspections for Midbay Fastener Locations 

As an option to confirm cracks found 

between tear straps during the inspections 

required by paragraph (g) of this AD, do an 

internal mid-frequency eddy current (MFEC) 

inspection for cracking in the lap joint 

fastener row between tear straps of the crown 

lap and do a detailed inspection of the lap 

joint lower fastener row for cracking, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1255, Revision 2, dated August 7, 

2012. 

(i) Internal Crown Lap Joint Inspection and 

Repair 

For airplanes on which the lap splice 

modification specified in AD 2002–07–08, 

Amendment 39–12702 (67 FR 17917, April 

12, 2002), has not been accomplished: At the 

times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1255, Revision 2, dated 

August 7, 2012, except as required by 

paragraphs (l)(1) and (l)(2) of this AD, do an 

internal MFEC, low frequency eddy current 

(LFEC), and detailed inspection for cracking 

in the crown lap joints and stringer clips, 

except as provided by paragraph (j) of this 

AD, in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1255, Revision 2, dated August 7, 

2012. 

(1) If any cracking is found in any lap joint, 

before further flight, repair, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1255, 

Revision 2, dated August 7, 2012. 

(2) If any cracking is found in any stringer 

clip, before further flight, replace the stringer 

clip with a new stringer clip, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1255, 

Revision 2, dated August 7, 2012. 

(j) Optional Inspections for Tear Strap 

Locations Only 

As an option to confirm cracks found at 

tear strap locations while doing the 

inspections required by paragraph (g) or (i) of 

this AD, do an open-hole inspection for 

cracking at the tear strap locations, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1255, Revision 2, dated August 7, 

2012. 

(k) Terminating Action 

(1) Accomplishing a repair of a crown lap 

joint in accordance with Boeing Alert Service 

Bulletin 737–53A1255, Revision 2, dated 

August 7, 2012, terminates the inspections 

required by paragraphs (g) and (i) of this AD 

for the repaired area only. 

(2) Accomplishing the modification of the 

crown lap joints in accordance with any of 

the service bulletins specified in paragraphs 

(k)(2)(i), (k)(2)(ii), and (k)(2)(iii) of this AD 

terminates the inspections required by 

paragraphs (g) and (i) of this AD for the 

modified area only. 

(i) Boeing Service Bulletin 737–53A1177, 

Revision 4, dated September 2, 1999. 

(ii) Boeing Service Bulletin 737–53A1177, 

Revision 5, dated February 15, 2001. 

(iii) Boeing Service Bulletin 737–53A1177, 

Revision 6, dated May 31, 2001. 

(l) Exceptions to Service Information 

(1) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1255, 

Revision 2, dated August 7, 2012, specifies a 

compliance time ‘‘from the Revision 1 date 

of this service bulletin,’’ this AD requires a 

compliance time ‘‘after the effective date of 

this AD.’’ 

(2) Where the ‘‘Condition’’ column, in 

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

Alert Service Bulletin 737–53A1255, 

Revision 2, dated August 7, 2012, specifies 

airplanes with certain flight cycles ‘‘at the 

Revision 1 date of this service bulletin,’’ for 

this AD the condition is for airplanes with 

corresponding flight cycles ‘‘as of the 

effective date of this AD.’’ 

(m) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g), (h), (i), 

and (j) of this AD, if those actions were 

performed before the effective date of this AD 

using Boeing Alert Service Bulletin 737– 

53A1255, Revision 1, dated November 7, 

2011, which is not incorporated by reference 

in this AD. 

(n) 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 the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-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, 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) AMOCs approved for paragraphs (a), 

(b), (c), (d), (e), (g), and (h) of AD 2002–07– 

08, Amendment 39–12702 (67 FR 17917, 

April 12, 2002), before the effective date of 

this AD, are approved for the corresponding 

requirements of paragraphs (g), (i), and (k) of 

this AD. 

(5) As of the effective date of this AD, any 

AMOCs approved for paragraphs (g) and (i) 

of this AD are approved as AMOCs for the 

corresponding requirements of paragraphs 

(a), (b), (c), (d), and (e) of AD 2002–07–08, 

Amendment 39–12702 (67 FR 17917, April 

12, 2002). 

(6) As of the effective date of this AD, 

installation of STC SA2969SO (http://rgl.faa.

gov/Regulatory_and_Guidance_Library/ 

rgstc.nsf/0/

2A10F5D4090A534686257A79006F0F97?

OpenDocument&Highlight=stc sa2969so) is 

approved as an AMOC for the corresponding 

requirements of paragraphs (g) and (i) of this 

AD from stringer S–3R to S–23L between 

body station (BS) 312 and BS 500B only. 

(o) Related Information 

(1) For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6447; fax: 425–917–6590; 

email: wayne.lockett@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. 

(p) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 78, No. 90 / Thursday, May 9, 2013 / Rules and Regulations 27005 

(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 June 13, 2013. 

(i) Boeing Alert Service Bulletin 737– 

53A1255, Revision 2, dated August 7, 2012. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on May 17, 2002 (67 FR 

17917, April 12, 2002). 

(i) Boeing Service Bulletin 737–53A1177, 

Revision 4, dated September 2, 1999. 

(ii) Boeing Service Bulletin 737–53A1177, 

Revision 5, dated February 15, 2001. 

(iii) Boeing Service Bulletin 737–53A1177, 

Revision 6, dated May 31, 2001. 

(5) 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. 

(6) You may review copies of the 

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. 

(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/ 

ibr-locations.html. 

Issued in Renton, Washington, on April 18, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–10005 Filed 5–8–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0845; Directorate 

Identifier 2012–CE–013–AD; Amendment 

39–17431; AD 2013–08–14] 

RIN 2120–AA64 

Airworthiness Directives; Revo, 

Incorporated Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain Revo, Incorporated Models 

COLONIAL C–1, COLONIAL C–2, LAKE 

LA–4, LAKE LA–4A, LAKE LA–4P, and 

LAKE LA–4–200 airplanes. That AD 

currently requires a one-time, dyepenetrant inspection of the horizontal 

stabilizer attachment fitting and 

repetitive visual inspections of the 

fitting for any evidence of fretting, 

cracking, or corrosion (with necessary 

replacement and modification); 

replacement of the fitting upon reaching 

the 850-hours time-in-service (TIS) safe 

life; and reporting to the FAA the results 

of the initial inspection and any cracks 

found on repetitive inspections. This 

new AD requires the same actions of AD 

2005–12–02 except using revised 

service documents and procedures, adds 

Model COLONIAL C–1 airplanes to the 

Applicability, and adds an optional 

terminating action for the requirements. 

This AD was prompted by a report from 

Revo, Incorporated that, while the 

drawing numbers are different, the 

attachment fittings on the Model 

COLONIAL C–1 airplanes are identical 

in every other respect to those installed 

on the airplanes referenced in AD 2005– 

12–02. We are issuing this AD to correct 

the unsafe condition on these products. 

DATES: This AD is effective June 13, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of June 13, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

the AD as of July 8, 2005 (70 FR 33820, 

June 10, 2005). 

ADDRESSES: For service information 

identified in this AD, contact Revo, 

Incorporated, 1396 Grandview 

Boulevard, Kissimmee, FL 34744; 

telephone: (407) 847–8080; email: 

support@teamlake.com; Lake Central 

Air Services, Muskoka Airport, R. R. #1, 

Gravenhurst, Ontario, Canada P1P 1R1; 

telephone: (705) 687–4343; email: 

akecent@muskoka.com; Internet: 

www.lakecentral.com; and Robert L. 

Copeland (XLS Co., LLC), 418B Bartow 

Municipal Airport, Bartow, FL 33830; 

FAA Aerospace Engineer (Hal 

Horsburgh), telephone: (404) 474–5553. 

You may review copies of the 

referenced service information at the 

FAA, Small Airplane Directorate, 901 

Locust St., Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call (816) 329– 

4148. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; 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: Hal 

Horsburgh, Aerospace Engineer, Atlanta 

Aircraft Certification Office, FAA, 1701 

Columbia Avenue, College Park, Georgia 

30337; phone: (404) 474–5553; fax: (404) 

474–5606; email: 

hal.horsburgh@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2005–12–02, 

amendment 39–14118 (70 FR 33820, 

June 10, 2005). That AD applies to the 

specified products. The NPRM 

published in the Federal Register on 

August 16, 2012 (77 FR 49389). That 

NPRM proposed to require the same 

actions of AD 2005–12–02, add Model 

COLONIAL C–1 airplanes to the 

Applicability, and add an optional 

terminating action for the requirements. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 49389, August 16, 2012) or on the 

determination of the cost to the public. 

We did notice that the date for XLS 

Company’s instructions for continued 

airworthiness was incorrect. We also 

identified the need to clarify giving 

credit for work done following previous 

service documents and procedures so 

the actions would not be unnecessarily 

duplicated. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for a typographical 

error in the date for XLS Company’s 

instructions for continued 

airworthiness, clarification of credit 

allowed for work done following 

previous service documents and 

procedures, and minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (August 16, 

2012, 77 FR 49389) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 


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