43766 Federal Register / Vol. 78, No. 140 / Monday, July 22, 2013 / Rules and Regulations 

(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 in the outboard flange of the 

longeron extension fittings, which attach to 

the wing-to-body fairing support frame. We 

are issuing this AD to detect and correct 

cracks in the longeron extension fittings, 

which can become large and adversely affect 

the structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection of Longeron Extension Fitting 

For all airplanes: Except as required by 

paragraphs (i)(1) and (i)(4) of this AD, at the 

time specified in table 1 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2860, dated December 4, 

2012, do a surface high frequency eddy 

current (HFEC) inspection of the left and 

right longeron extension fittings for cracking, 

and do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2860, dated December 4, 2012, 

except as required by paragraphs (i)(2) and 

(i)(3) of this AD. Do all applicable corrective 

actions before further flight. If no cracking is 

found, repeat the inspection thereafter at the 

intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2860, dated December 4, 

2012, until a permanent repair, longeron 

extension fitting replacement, or preventative 

modification is done, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2860, dated 

December 4, 2012. 

(h) Inspection of Temporary Repair and 

Corrective Actions 

For airplanes on which a temporary repair 

as specified in Boeing Alert Service Bulletin 

747–53A2860 has been done: At the times 

specified in table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2860, dated December 4, 

2012, do a surface HFEC inspection of the 

temporary repair of the longeron extension 

fittings for cracking, and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2860, dated 

December 4, 2012, except as required by 

paragraph (i)(3) of this AD. Do all applicable 

corrective actions before further flight. 

(i) Exceptions to Service Information 

(1) Where Boeing Alert Service Bulletin 

747–53A2860, dated December 4, 2012, 

specifies a compliance time relative to the 

issue date of that service bulletin, this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where Boeing Alert Service Bulletin 

747–53A2860, dated December 4, 2012, 

specifies to contact Boeing for repair 

information: Before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (k) of 

this AD. 

(3) For airplanes not identified in Boeing 

Alert Service Bulletin 747–53A2860, dated 

December 4, 2012, but included in paragraph 

(c) of this AD: These airplanes are in Group 

1 for the purposes of this AD. This AD 

requires that the applicable actions specified 

in the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2860, 

dated December 4, 2012, be accomplished on 

these airplanes. 

(4) Where Boeing Alert Service Bulletin 

747–53A2860, dated December 4, 2012, 

specifies ‘‘all airplanes,’’ this means all 

airplanes identified in paragraph (c) of this 

AD. 

(j) Optional Terminating Action 

Doing the permanent repair, longeron 

extension fitting replacement, or preventative 

modification, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2860, dated 

December 4, 2012, terminates the repetitive 

inspections required by paragraph (g) of this 

AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office, 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. 

(l) Related Information 

For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, Washington 

98057–3356; phone: 425–917–6428; fax: 425– 

917–6590; email: 

Nathan.P.Weigand@faa.gov. 

(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 747– 

53A2860, dated December 4, 2012. 

(ii) Reserved. 

(3) 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. 

(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 June 25, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Manager, Transport 

Airplane Directorate, Aircraft Certification 

Service. 

[FR Doc. 2013–17137 Filed 7–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0206; Directorate 

Identifier 2012–NM–068–AD; Amendment 

39–17507; AD 2013–14–02] 

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 all The 

Boeing Company Model 727 airplanes. 

This AD was prompted by reports of 

spanwise cracks and corrosion in the 

wing center box upper skin and rear 

spar upper chord between left buttock 

line (LBL) 70.50 and right buttock line 

(RBL) 70.50 at body station (STA) 870. 

This AD requires repetitive inspections 

of the wing center box for cracking 

around certain fastener rows on the rear 

spar upper chord horizontal flange; for 

certain airplanes, repetitive inspections 

for cracking of the rear spar upper chord 

radius; for certain other airplanes, 

repetitive inspections for damage, 

cracking, and corrosion of the pressure 


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Federal Register / Vol. 78, No. 140 / Monday, July 22, 2013 / Rules and Regulations 43767 

seal; and repair if necessary. We are 

issuing this AD to detect and correct 

cracking and corrosion of the upper skin 

and rear spar upper chord of the wing 

center box, which could result in loss of 

the airplane wing and consequent loss 

of control of the airplane. 

DATES: This AD is effective August 26, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of August 26, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https:// 

www.myboeingfleet.com. You may 

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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: (425) 917–6577; 

fax: (425) 917–6590; email: 

berhane.alazar@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on March 12, 2013 (78 FR 

15658). The NPRM proposed to require 

repetitive inspections of the wing center 

box for cracking around certain fastener 

rows on the rear spar upper chord 

horizontal flange; for certain airplanes, 

repetitive inspections for cracking of the 

rear spar upper chord radius; for certain 

other airplanes, repetitive inspections 

for damage, cracking, and corrosion of 

the pressure seal; and repair if 

necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Supportive Comments 

Boeing stated that it supports the 

NPRM (78 FR 15658, March 12, 2013). 

FedEx stated that the requirements 

proposed in the NPRM (78 FR 15658, 

March 12, 2013) would fit within the 

planned scheduled maintenance check 

and not impact fleet availability or spantime of the planned scheduled 

maintenance check. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed—except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

15658, March 12, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 15658, 

March 12, 2013). 

Costs of Compliance 

We estimate that this AD affects 98 

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 

Inspection ......... 67 work-hours × $85 per hour = $5,695 per inspection cycle.$0 $5,695 per inspection 

cycle.

$558,110 per inspection 

cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this 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, 


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43768 Federal Register / Vol. 78, No. 140 / Monday, July 22, 2013 / Rules and Regulations 

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): 

2013–14–02 The Boeing Company: 

Amendment 39–17507 ; Docket No. FAA– 

2013–0206; Directorate Identifier 2012– 

NM–068–AD. 

(a) Effective Date 

This AD is effective August 26, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 727, 727C, 727–100, 727– 

100C, 727–200, and 727–200F series 

airplanes, certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

spanwise cracks and corrosion in the wing 

center box upper skin and rear spar upper 

chord between left buttock line (LBL) 70.50 

and right buttock line (RBL) 70.50 at body 

station (STA) 870. We are issuing this AD to 

detect and correct cracking and corrosion of 

the upper skin and rear spar upper chord of 

the wing center box, which could result in 

loss of the airplane wing and consequent loss 

of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Except as specified in paragraph (h) of this 

AD, at the applicable time specified in 

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

Special Attention Service Bulletin 727–57– 

0187, dated March 8, 2012: Inspect the wing 

center box between LBL 70.50 and RBL 

70.50, at STA 870, as specified in paragraphs 

(g)(1), (g)(2), (g)(3), (g)(4), and (g)(5) of this 

AD, as applicable, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 727–57– 

0187, dated March 8, 2012. Repeat the 

inspections thereafter at the applicable times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

727–57–0187, dated March 8, 2012. If any 

crack, corrosion, or damage is found during 

any inspection required by this AD, before 

further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (i) of this AD. 

(1) Do a high frequency eddy current 

(HFEC) or detailed inspection for cracking 

around the forward fastener row in the rear 

spar upper chord horizontal flange. 

(2) Do a low frequency eddy current 

inspection for cracking around the aft 

fastener row in the rear spar upper chord 

horizontal flange. 

(3) Do a detailed or HFEC inspection for 

cracking in the rear spar upper chord radius. 

(4) Do a detailed or HFEC inspection for 

cracking in the upper skin around the 

forward fastener row common to the rear spar 

upper chord horizontal flange. 

(5) Do a detailed inspection for damage, 

cracking, and corrosion in the pressure seal. 

(h) Exception to the Service Information 

Boeing Special Attention Service Bulletin 

727–57–0187, dated March 8, 2012, specifies 

compliance times ‘‘after the original issue 

date of this service bulletin.’’ However, this 

AD requires compliance within the specified 

compliance times ‘‘after the effective date of 

this AD.’’ 

(i) 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. 

(j) Related Information 

For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

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

email: berhane.alazar@faa.gov. 

(k) 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 Special Attention Service 

Bulletin 727–57–0187, dated March 8, 2012. 

(ii) Reserved. 

(3) 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. 

(4) You may view this service information 

at 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 June 21, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–16927 Filed 7–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0213; Directorate 

Identifier 2012–NM–207–AD; Amendment 

39–17512; AD 2013–14–07] 

RIN 2120–AA64 

Airworthiness Directives; Learjet Inc. 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Learjet Inc. Model 45 airplanes. This AD 

was prompted by a report that the fire 

barrier seal on the external baggage door 

does not seal the surrounding door 

structure due to incorrect positioning of 

the barrier. This AD requires modifying 

the fire seal on the baggage door, 

including doing inspections of the fire 

seal for correct contact and corrective 

action if necessary. We are issuing this 

AD to prevent improper sealing of the 

baggage door, which could increase the 

risk of an uncontained fire in the 

baggage compartment. 

DATES: This AD is effective August 26, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of August 26, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Learjet, 


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