7374 Federal Register / Vol. 79, No. 26 / Friday, February 7, 2014 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0691; Directorate 

Identifier 2012–NM–170–AD; Amendment 

39–17678; AD 2013–24–04] 

RIN 2120–AA64 

Airworthiness Directives; Learjet Inc. 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2003–19– 

11 for certain Learjet Inc. Model 60 

airplanes. AD 2003–19–11 required 

determining if a certain fuel crossflow 

tube is installed; and follow-on/

corrective actions, as applicable. This 

new AD requires retaining all actions in 

AD 2003–19–11, and it also requires 

determining if a certain fuel crossflow 

tube is installed, performing repetitive 

measurements of the fuel crossflow tube 

and surrounding valves and cables, and 

doing corrective actions if necessary. In 

addition, this new AD expands the 

applicability of AD 2003–19–11. This 

AD was prompted by a report that 

airplanes produced since 2003 might 

also be subject to the unsafe condition; 

and that the minimum allowable 

clearance is not established in the 

airplane maintenance information. We 

are issuing this AD to prevent chafing 

and consequent failure of the fuel 

crossflow tube due to inadequate 

clearance between the tube and the 

flight control cables, which could result 

in loss of fuel from one fuel tank during 

normal operating conditions or loss of 

fuel from both main fuel tanks during 

fuel cross-feeding operations. 

DATES: This AD is effective March 14, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 3, 2003 (68 FR 55812, 

September 29, 2003). 

ADDRESSES: For service information 

identified in this AD, contact Learjet, 

Inc., One Learjet Way, Wichita, KS 

67209–2942; telephone 316–946–2000; 

fax 316–946–2220; email ac.ict@

aero.bombardier.com; Internet http://

www.bombardier.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/#!docketBrowser;rpp=25;po=0;D=

FAA-2013-0691; 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 

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 20590. 

FOR FURTHER INFORMATION CONTACT: Jeff 

Janusz, Aerospace Engineer, Propulsion 

Branch, ACE–116W, FAA, Wichita 

Aircraft Certification Office (ACO), 1801 

Airport Road, Room 100, Wichita, KS 

67209; phone: 316–946–4148; fax: 316– 

946–4107; email: jeff.janusz@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2003–19–11, 

Amendment 39–13314 (68 FR 55812, 

September 29, 2003). AD 2003–19–11 

applied to certain Learjet Inc. Model 60 

airplanes. The NPRM published in the 

Federal Register on August 13, 2013 (78 

FR 49232). The NPRM was prompted by 

a report that airplanes produced since 

2003 might also be subject to the unsafe 

condition; and that the minimum 

allowable clearance is not established in 

the airplane maintenance information. 

The NPRM proposed to continue to 

require determining if a certain fuel 

crossflow tube is installed; and followon/corrective actions, as applicable. The 

NPRM also proposed to require 

determining if a certain fuel crossflow 

tube is installed, performing repetitive 

measurements of the fuel crossflow tube 

and surrounding valves and cables, and 

doing corrective actions if necessary. In 

addition, the NPRM proposed to expand 

the applicability of AD 2003–19–11. We 

are issuing this AD to prevent chafing 

and consequent failure of the fuel 

crossflow tube due to inadequate 

clearance between the tube and the 

flight control cables, which could result 

in loss of fuel from one fuel tank during 

normal operating conditions or loss of 

fuel from both main fuel tanks during 

fuel cross-feeding operations. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 49232, August 13, 2013) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data 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 

49232, August 13, 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 49232, 

August 13, 2013). 

Costs of Compliance 

We estimate that this AD affects 264 

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 [retained actions from AD 2003–19– 

11, Amendment 39–13314 (68 FR 55812, 

September 29, 2003)].

2 work-hours × $85 per hour = $170 ................... $2 $172 $45,408 

We estimate the following costs to do 

any necessary replacement that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need this replacement: 

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Federal Register / Vol. 79, No. 26 / Friday, February 7, 2014 / Rules and Regulations 7375 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement .................................... 4 work-hours × $85 per hour = $340 ........................................................ $20 $360 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591. ATTN: Information 

Collection Clearance Officer, AES–200. 

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) 

2003–19–11, Amendment 39–13314 (68 

FR 55812, September 29, 2003), and 

adding the following new AD: 

2013–24–04 Learjet Inc.: Amendment 39– 

17678; Docket No. FAA–2013–0691; 

Directorate Identifier 2012–NM–170–AD. 

(a) Effective Date 

This AD is effective March 14, 2014. 

(b) Affected ADs 

This AD supersedes AD 2003–19–11, 

Amendment 39–13314 (68 FR 55812, 

September 29, 2003). 

(c) Applicability 

This AD applies to Learjet Inc. Model 60 

airplanes, certificated in any category, serial 

numbers 60–001 through 60–409 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by a report that 

airplanes produced since 2003 might also be 

subject to the unsafe condition; and that the 

minimum allowable clearance is not 

established in the airplane maintenance 

information. We are issuing this AD to 

prevent chafing and consequent failure of the 

fuel crossflow tube due to inadequate 

clearance between the tube and the flight 

control cables, which could result in loss of 

fuel from one fuel tank during normal 

operating conditions or loss of fuel from both 

main fuel tanks during fuel cross-feeding 

operations. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Part Identification for Airplanes 

Having Serial Numbers 60–001 Through 

60–145 Inclusive 

This paragraph restates the part 

identification required by paragraph (a) of 

AD 2003–19–11, Amendment 39–13314 (68 

FR 55812, September 29, 2003). For airplanes 

having serial numbers 60–001 through 60– 

145 inclusive: Within 25 flight hours after 

November 3, 2003 (the effective date of AD 

2003–19–11), inspect the fuel crossflow tube 

to determine whether part number (P/N) 

6026020–005 is installed. Instead of 

inspecting the tube, a review of airplane 

maintenance records is acceptable if the part 

number of the tube can be positively 

determined from that review. 

(h) Retained Clearance Measurement and 

Corrective Action for Airplanes Having 

Serial Numbers 60–001 Through 60–145 

Inclusive, With Revised Repair Language 

This paragraph restates the clearance 

measurement and corrective action required 

by paragraph (b) of AD 2003–19–11, 

Amendment 39–13314 (68 FR 55812, 

September 29, 2003), with revised repair 

language. For airplanes having serial 

numbers 60–001 through 60–145 inclusive: If 

P/N 6026020–005 is found installed during 

the review or inspection required by 

paragraph (g) of this AD, before further flight, 

measure the clearance between the fuel 

crossflow tube and the flight control cables 

to determine if it is at least 0.35 inch, per 

paragraph 2.B.(8) of the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin A60–28–3, Revision 2, dated 

October 26, 1998. 

(1) If the clearance is 0.35 inch or more, no 

further action is required by this paragraph. 

(2) If the clearance is less than 0.35 inch, 

before further flight, repair in accordance 

with a method approved by the Manager, 

Wichita Aircraft Certification Office (ACO), 

FAA. For a repair method to be approved by 

the Manager, Wichita ACO, as required by 

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7376 Federal Register / Vol. 79, No. 26 / Friday, February 7, 2014 / Rules and Regulations 

this paragraph, the Manager’s approval letter 

must specifically refer to this AD. 

Note 1 to paragraphs (h) and (j) of this AD: 

Bombardier Alert Service Bulletin A60–28–3, 

Revision 2, dated October 26, 1998, Figure 1, 

Detail D, incorrectly identifies the fuel 

crossflow tube to be installed as P/N 

6026020–001. The manufacturer is aware of 

this error and stated it plans to correct the 

part number in the next revision of the 

service information. 

(i) Retained Part Replacement, 

Measurement, and Repair for Airplanes 

Having Serial Numbers 60–001 Through 

60–055 Inclusive, With Revised Repair 

Language 

This paragraph restates the part 

replacement, clearance measurement, and 

corrective action required by paragraph (c) of 

AD 2003–19–11, Amendment 39–13314 (68 

FR 55812, September 29, 2003), with revised 

repair language. For airplanes having serial 

numbers 60–001 through 60–055 inclusive: If 

P/N 6026020–005 is not found installed 

during the review or inspection required by 

paragraph (g) of this AD, within 90 days after 

accomplishing the review or inspection, 

replace the existing fuel crossflow tube with 

a new fuel crossflow tube having P/N 

6026020–005, and measure the clearance 

between the newly installed fuel crossflow 

tube and the flight control cables, per 

paragraph 2.A. of the Accomplishment 

Instructions of Bombardier Service Bulletin 

60–28–4, Revision 2, dated August 22, 2001. 

(1) If the clearance is 0.35 inch or more, no 

further action is required by this paragraph. 

(2) If the clearance is less than 0.35 inch, 

before further flight, repair in accordance 

with a method approved by the Manager, 

Wichita ACO, FAA. For a repair method to 

be approved by the Manager, Wichita ACO, 

as required by this paragraph, the Manager’s 

approval letter must specifically refer to this 

AD. 

(j) Retained Part Replacement, 

Measurement, and Repair for Airplanes 

Having Serial Numbers 60–056 Through 

60–145 Inclusive, With Revised Repair 

Language 

This paragraph restates the part 

replacement, clearance measurement, and 

corrective action required by paragraph (d) of 

AD 2003–19–11, Amendment 39–13314 (68 

FR 55812, September 29, 2003), with revised 

repair language. For airplanes having serial 

numbers 60–056 through 60–145 inclusive: If 

P/N 6026020–005 is not found installed 

during the review or inspection required by 

paragraph (g) of this AD, within 90 days after 

accomplishing the review or inspection, 

replace the existing fuel crossflow tube with 

a new fuel crossflow tube having P/N 

6026020–005, and measure the clearance 

between the newly installed fuel crossflow 

tube and the flight control cables to 

determine if the clearance is at least 0.35 

inch, per paragraph 2.B. of the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin A60–28–3, Revision 2, 

dated October 26, 1998. 

(1) If the clearance is 0.35 inch or more, no 

further action is required by this paragraph. 

(2) If the clearance is less than 0.35 inch, 

before further flight, repair in accordance 

with a method approved by the Manager, 

Wichita ACO, FAA. For a repair method to 

be approved by the Manager, Wichita ACO, 

as required by this paragraph, the Manager’s 

approval letter must specifically refer to this 

AD. 

(k) New Part Identification 

For airplanes having serial numbers 60– 

001 through 60–409 inclusive: Within 25 

flight hours after the effective date of this AD, 

inspect the fuel crossflow tube to determine 

whether P/N 6026020–005 is installed. In 

lieu of inspecting the tube, a review of 

airplane maintenance records is acceptable if 

the part number of the tube can be positively 

determined from that review. 

(l) New Clearance Measurement 

If P/N 6026020–005 is found installed 

during the inspection required by paragraph 

(k) of this AD, before further flight, measure 

the clearance between the fuel crossflow tube 

and both elevator control cables to determine 

if it is 0.35 inch or more, in accordance with 

paragraph 2.A.(9) of the Accomplishment 

Instructions of Bombardier Service Bulletin 

60–28–4, Revision 2, dated August 22, 2001. 

(1) If the clearance is 0.35 inch or more, no 

further action is required by this paragraph. 

(2) If the clearance is less than 0.35 inch, 

before further flight, adjust the fit of the P/ 

N 6026020–005 tube to provide 0.35 inch or 

more clearance to both elevator control 

cables, in accordance with paragraph 2.A.(9) 

of the Accomplishment Instructions of 

Bombardier Service Bulletin 60–28–4, 

Revision 2, dated August 22, 2001. If the tube 

shows any indication of chafing from the 

control cables, before further flight, replace 

the fuel crossflow tube with a new fuel 

crossflow tube, in accordance with paragraph 

2.A.(9) of the Accomplishment Instructions 

of Bombardier Service Bulletin 60–28–4, 

Revision 2, dated August 22, 2001. 

(m) New Repetitive Measurements 

For all airplanes: As of the effective date 

of this AD and after accomplishing the 

inspection required by paragraph (g) or (k) of 

this AD, as applicable: Before further flight 

after removal, replacement, or adjustment of 

any crossflow tube, fuel crossflow drain 

valve, fuel crossflow valve or related 

plumbing and fittings, and elevator control 

cable, measure the clearance between the fuel 

crossflow tube and the flight control cables, 

in accordance with paragraph 2.A.(9) of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 60–28–4, Revision 2, dated 

August 22, 2001. 

(1) If the clearance is 0.35 inch or more, no 

further action is required by this paragraph. 

(2) If the clearance is less than 0.35 inch, 

before further flight, adjust the fit of the P/ 

N 6026020–005 tube to provide 0.35 inch or 

more clearance to both elevator control 

cables, in accordance with paragraph 2.A.(9) 

of the Accomplishment Instructions of 

Bombardier Service Bulletin 60–28–4, 

Revision 2, dated August 22, 2001. 

(n) Reporting Requirement 

Submit a report of the findings of the 

initial measurement required by paragraph (l) 

of this AD to the Wichita Manufacturing 

Inspection District Office, 2204 South Tyler 

Road, Wichita, KS 67209–3001, at the 

applicable time specified in paragraph (n)(1) 

or (n)(2) of this AD. The report must include 

the airplane registration, serial number, the 

total time in service, and the measured 

clearance found between the fuel crossflow 

tube and the elevator control cables after the 

initial inspection. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(o) Part Installation Prohibition 

As of the effective date of AD, only fuel 

crossflow tubes having P/N 6026020–005 

may be installed on any airplane. 

(p) Paperwork Reduction Act Burden 

Statement 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 5 minutes per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave. SW., Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

(q) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (r) of this AD. 

(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. 

(r) Related Information 

For more information about this AD, 

contact Jeff Janusz, Aerospace Engineer, 

Propulsion Branch, ACE–116W, FAA, 

Wichita ACO, 1801 Airport Road, Room 100, 

Wichita, KS 67209; phone: 316–946–4148; 

fax: 316–946–4107; email: jeff.janusz@

faa.gov. 

(s) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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Federal Register / Vol. 79, No. 26 / Friday, February 7, 2014 / Rules and Regulations 7377 

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 November 3, 2003 (68 

FR 55812, September 29, 2003). 

(i) Bombardier Alert Service Bulletin A60– 

28–3, Revision 2, dated October 26, 1998. 

(ii) Bombardier Service Bulletin 60–28–4, 

Revision 2, dated August 22, 2001. 

(4) For service information identified in 

this AD, contact Learjet, Inc., One Learjet 

Way, Wichita, KS 67209–2942; telephone 

316–946–2000; fax 316–946–2220; email 

ac.ict@aero.bombardier.com; Internet http://

www.bombardier.com. 

(5) 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. 

(6) 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 

December 27, 2013. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–02464 Filed 2–6–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0538; Directorate 

Identifier 2012–NM–212–AD; Amendment 

39–17728; AD 2014–01–05] 

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 737–100, 

–200, –200C, –300, –400, and –500 

series airplanes. This AD was prompted 

by a report of cracks in stringer splices 

at body station STA 360 and STA 908, 

between stringer (S) S–10L and S–10R; 

cracks in butt straps between S–5L and 

S–3L, and 

S–3R and S–5R; vertical chem-mill 

fuselage skin cracks at certain butt 

joints; and an instance of cracking that 

occurred in all those three structural 

elements on one airplane. This AD 

requires repetitive inspections for any 

cracking of stringer splices and butt 

straps, and related corrective and 

investigative actions if necessary. We 

are issuing this AD to detect and correct 

cracking in the three structural 

elements, which could result in the 

airplane not being able to sustain limit 

load requirements and possibly result in 

uncontrolled decompression. 

DATES: This AD is effective March 14, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 14, 2014. 

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 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–2013– 

0538; 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 

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 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 by adding an AD that would 

apply to certain The Boeing Company 

Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes. The 

NPRM published in the Federal 

Register on June 27, 2013 (78 FR 38608). 

The NPRM was prompted by a report of 

cracks in stringer splices at body station 

STA 360 and STA 908, between stringer 

(S) S–10L and S–10R; cracks in butt 

straps between S–5L and S–3L, and 

S–3R and S–5R; vertical chem-mill 

fuselage skin cracks at certain butt 

joints; and an instance of cracking that 

occurred in all those three structural 

elements on one airplane. The NPRM 

proposed to require repetitive 

inspections for any cracking of stringer 

splices and butt straps, and related 

corrective and investigative actions if 

necessary. We are issuing this AD to 

detect and correct cracking in the three 

structural elements, which could result 

in the airplane not being able to sustain 

limit load requirements and possibly 

result in uncontrolled decompression. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 38608, 

June 27, 2013) and the FAA’s response 

to each comment. 

Request to Clarify That Post-Repair 

Inspections Are Not Required by This 

Final Rule 

Boeing requested clarification that 

Table 11, ‘‘Stringer Splice Post Repair 

Inspection,’’ in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1322, dated November 

5, 2012, is not required by paragraph (h) 

of the NPRM (78 FR 38608, June 27, 

2013). Boeing suggested that paragraph 

(h) of the NPRM be revised to include 

an exception phrase that references 

paragraph (i) of the NPRM. Boeing 

stated that the inspections specified in 

Table 11, ‘‘Stringer Splice Post Repair 

Inspection,’’ in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1322, dated November 

5, 2012, are required to support 

operating requirements for complying 

with section 121.1109(c)(2) or 

129.109(b)(2) of the Federal Aviation 

Regulations (14 CFR 121.1109(c)(2) or 

14 CFR 129.109(b)(2)). Boeing also 

stated that the way the sentences of 

paragraph (h) of the NPRM are arranged, 

the sentences for doing corrective 

actions and repeating inspections seem 

to link the corrective actions and the 

repetitive inspections and imply that 

Table 11, ‘‘Stringer Splice Post Repair 

Inspection,’’ in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1322, dated November 

5, 2012, is required by both the NPRM 

and the Federal Aviation Regulations. 

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