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

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Rules and Regulations Federal Register

35479 

Vol. 79, No. 120 

Monday, June 23, 2014 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0141; Directorate 

Identifier 2013–NM–024–AD; Amendment 

39–17871; AD 2014–12–10] 

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 727–100 

series airplanes. This AD is intended to 

complete certain mandated programs 

intended to support the airplane 

reaching its limit of validity (LOV) of 

the engineering data that support the 

established structural maintenance 

program. For certain airplanes, this AD 

requires repetitive inspections for 

cracking in stringers or frames until 

modification, and repair if necessary. 

We are issuing this AD to detect and 

correct cracking in stringers or frames 

originating at or near stringer-to-frame 

attachment fastener holes, which could 

result in reduced structural integrity of 

the airplane, and decompression of the 

cabin. 

DATES: This AD is effective July 28, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 28, 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–2014– 

0141; 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: 

Chandra Ramdoss, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

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 727–100 series airplanes. The 

NPRM published in the Federal 

Register on March 12, 2014 (79 FR 

13931). The NPRM proposed actions 

intended to complete certain mandated 

programs intended to support the 

airplane reaching its limit of validity 

(LOV) of the engineering data that 

support the established structural 

maintenance program. For certain 

airplanes, the NPRM proposed to 

require repetitive inspections for 

cracking in stringers or frames until 

modification, and repair if necessary. 

We are issuing this AD to detect and 

correct cracking in stringers or frames 

originating at or near stringer-to-frame 

attachment fastener holes, which could 

result in reduced structural integrity of 

the airplane, and decompression of the 

cabin. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 13931, March 12, 2014) 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 (79 FR 

13931, March 12, 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 13931, 

March 12, 2014). 

Costs of Compliance 

We estimate that this AD affects 2 

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 

Inspections ........... 60 work-hours × $85 per hour = $5,100 per inspection 

cycle.

$0 $5,100 per inspection cycle $10,200 per inspection cycle. 


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35480 Federal Register / Vol. 79, No. 120 / Monday, June 23, 2014 / Rules and Regulations 

We estimate the following costs to do 

any necessary modifications that would 

be required based on the results of the 

inspections. We have no way of 

determining the number of aircraft that 

might need these modifications: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Modification .......... 600 work-hours × $85 per hour = $51,000 per inspection cycle ..... Up to $11,481 ............................. Up to $62,481 per 

modification. 

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): 

2014–12–10 The Boeing Company: 

Amendment 39–17871; Docket No. 

FAA–2014–0141; Directorate Identifier 

2013–NM–024–AD. 

(a) Effective Date 

This AD is effective July 28, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 727–100 series airplanes, certificated 

in any category, as identified in Boeing 

Service Bulletin 727–53–0041, Revision 6, 

dated September 5, 1991, unless previously 

modified using the service information 

specified in paragraphs (c)(1), (c)(2), or (c)(3) 

of this AD. 

(1) Boeing Service Bulletin 727–53–0041, 

Revision 4, dated July 27, 1973. 

(2) Boeing Service Bulletin 727–53–0041, 

Revision 5, dated January 25, 1990. 

(3) Boeing Service Bulletin 727–53–0041, 

Revision 6, dated September 5, 1991. 

Note 1 to paragraph (c) of this AD: Boeing 

Service Bulletin 727–53–0041, Revision 4, 

dated July 27, 1973, is specified in Boeing 

Document D6–54860 ‘‘Aging Airplane 

Service Bulletin Structural Modification 

Program—Model 727,’’ Revision C, dated 

December 11, 1989, as mandated by AD 90– 

06–09, Amendment 39–6488 (55 FR 8370, 

March 7, 1990). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD is intended to complete certain 

mandated programs intended to support the 

airplane reaching its limit of validity (LOV) 

of the engineering data that support the 

established structural maintenance program. 

We are issuing this AD to detect and correct 

cracking in stringers or frames originating at 

or near stringer-to-frame attachment fastener 

holes, which could result in reduced 

structural integrity of the airplane, and 

decompression of the cabin. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections 

Before the accumulation of 16,000 total 

flight cycles, or within 3,000 flight cycles 

after the effective date of this AD, whichever 

occurs later, do a high frequency eddy 

current inspection and a general visual 

inspection for cracking in stringers and 

frames originating at or near stringer-to-frame 

attachment fastener holes, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 727–53–0041, 

Revision 6, dated September 5, 1991. Repeat 

the inspections thereafter at intervals not to 

exceed 6,000 flight cycles until the 

modification specified by paragraph (h) of 

this AD is accomplished. If any crack is 

found during any inspection required by this 

paragraph: Before further flight, repair or 

modify the affected stringer-to-frame 

attachment locations, in accordance with Part 

V, ‘‘Repair Data,’’ of the Accomplishment 

Instructions of Boeing Service Bulletin 727– 

53–0041, Revision 6, dated September 5, 

1991. 

(h) Modification 

Modifying the affected stringer-to-frame 

attachment locations, in accordance with Part 

IV, ‘‘Preventive Modification Data,’’ of the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–53–0041, Revision 6, 

dated September 5, 1991, terminates the 

repetitive inspections required by paragraph 

(g) of this AD. 

(i) 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, 

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 (j) of this AD. Information may be 

emailed to: 9-ANM-LAACO-AMOCREQUESTS@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. 


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Federal Register / Vol. 79, No. 120 / Monday, June 23, 2014 / Rules and Regulations 35481 

(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 the 

approval must specifically refer to this AD. 

(j) Related Information 

For more information about this AD, 

contact Chandra Ramdoss, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles ACO, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5239; fax: 562–627–5210; 

email: chandraduth.ramdoss@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 Service Bulletin 727–53–0041, 

Revision 6, dated September 5, 1991. 

(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 4, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–13830 Filed 6–20–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0574; Directorate 

Identifier 2008–SW–22–AD; Amendment 39– 

17766; AD 2014–04–07] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada (Bell) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2003–05– 

03 for Bell Model 407 helicopters. AD 

2003–05–03 required preflight checking 

and repetitively inspecting for a crack in 

certain tailbooms that have been 

redesigned, replacing the tailboom if 

there is a crack, modifying and reidentifying certain tailbooms, installing 

an improved horizontal stabilizer 

assembly, and assigning a 5,000 hour 

time-in-service (TIS) limit. This new AD 

retains the requirements of AD 2003– 

05–03 and requires additional 

inspection requirements. This AD was 

prompted by additional reports of 

cracked tailboom skins. The actions in 

this AD are intended to prevent 

separation of the tailboom and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective July 28, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 28, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of April 17, 2003 (68 FR 

11967, March 13, 2003). 

ADDRESSES: For service information 

identified in this AD, contact Bell 

Helicopter Textron Canada, 12,800 Rue 

de l’Avenir, Mirabel, Quebec J7J1R4, 

telephone (450) 437–2862 or (800) 363– 

8023, fax (450) 433–0272 or at http://

www.bellcustomer.com/files/. You may 

review service information at the FAA, 

Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov in Docket No. 

FAA–2013–0574 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 foreign 

authority’s AD, any incorporated-byreference information, the economic 

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: 

Sharon Miles, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5110, fax 

(817) 222–5961, email sharon.y.miles@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2003–05–03 (68 

FR 11967, March 13, 2003). AD 2003– 

05–03 applied to Bell Model 407 

helicopters. The NPRM published in the 

Federal Register on July 12, 2013 (78 FR 

41877). The NPRM proposed to retain 

the actions of AD 2003–05–03 requiring 

preflight checks and repetitive 

inspections for a crack in certain 

tailbooms that have been redesigned, 

replacing the tailboom if there is a 

crack, modifying and re-identifying 

certain tailbooms, installing an 

improved horizontal stabilizer 

assembly, and assigning a 5,000 hour 

TIS limit. The NPRM also proposed to 

require additional inspection 

requirements. 

The NPRM was prompted by 

Canadian AD No. CF–2008–04, dated 

January 11, 2008 (AD CF–2008–04), 

issued by Transport Canada Civil 

Aviation (TCAA), which is the aviation 

authority for Canada, to correct an 

unsafe condition for Bell Model 407 

helicopters. TCAA advises that there 

have been several reports of cracks to 

the tailboom skin on the left side in the 

area of the horizontal stabilizer. AD CF– 

2008–04 mandates new inspection 

requirements based on the 

manufacturer’s service information 

discussed in the ‘‘Related Service 

Information’’ section under 

SUPPLEMENTARY INFORMATION in the 

preamble of this final rule. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 


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