12368 Federal Register / Vol. 79, No. 43 / Wednesday, March 5, 2014 / Rules and Regulations 

incorporating Modification Summary 

(ModSum) 4–113687, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–52–66, Revision A, dated 

October 24, 2011. 

(h) Revision of the Maintenance Program 

Schedule 

(1) Within 30 days after the effective date 

of this AD, revise the maintenance program 

by incorporating the information in 

maintenance Tasks 521200–105 and 524100– 

105 of Bombardier Temporary Revision (TR) 

ALI–122, dated November 4, 2011, into 

Section 1 Certification Maintenance 

Requirements of the Airworthiness 

Limitations Items (ALI) Part 2, Bombardier 

Q400 Dash 8 Maintenance Requirements 

Manual, PSM 1–84–7. The compliance time 

for doing the initial inspections of the handle 

shafts on the aft entry and service door is 

within 25,000 flight hours after installation of 

the new handle shaft specified in paragraph 

(g) of this AD. The flight hours specified in 

the tasks must be applied to the airplane 

service life, not to the handle service life. 

Thereafter, no alternative actions (e.g., 

inspections) or intervals may be used unless 

the actions or intervals are approved as an 

alternative method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (j)(1) of this AD. 

(2) The maintenance program revision 

required by paragraph (h)(1) of this AD may 

be done by inserting a copy of Bombardier 

TR ALI–122, dated November 4, 2011, into 

Section 1 Certification Maintenance 

Requirements of the Airworthiness 

Limitations Items (ALI) Part 2, Bombardier 

Q400 Dash 8 Maintenance Requirements 

Manual, PSM 1–84–7. When this TR has been 

included in general revisions of the 

maintenance requirements manual, the 

general revisions may be inserted in the 

maintenance requirements manual and this 

TR removed. 

(i) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Bombardier 

Service Bulletin 84–52–66, dated July 25, 

2011, which is not incorporated by reference 

in this AD. 

(2) This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if, through attrition, the handle shaft was 

replaced with a single-piece machined 

handle shaft having part number 85217916– 

115 or 85217916–116 before the effective 

date of this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531. 

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. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2012–17, dated 

May 24, 2012, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2012-1226-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

paragraphs (l)(3) and (l)(4) of this AD. 

(l) 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) Bombardier Service Bulletin 84–52–66, 

Revision A, dated October 24, 2011. 

(ii) Bombardier Temporary Revision ALI– 

122, dated November 4, 2011, to Section 1 

Certification Maintenance Requirements of 

the Airworthiness Limitations Items (ALI) 

Part 2, Bombardier Q400 Dash 8 Maintenance 

Requirements Manual, PSM 1–84–7. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.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 January 

22, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–02516 Filed 3–4–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0866; Directorate 

Identifier 2013–NM–131–AD; Amendment 

39–17743; AD 2014–03–06] 

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 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. This AD was prompted by 

reports of cracks found in the aft 

support fitting, the rear spar upper 

chord, and the rear spar web. This AD 

requires repetitive inspections for 

cracking of the aft support fitting for the 

main landing gear (MLG) beam, and the 

rear spar upper chord and rear spar web 

in the area of rear spar station (RSS) 

224.14; and repair if necessary. We are 

issuing this AD to detect and correct 

such cracks, which could grow and 

result in a fuel leak and possible fire. 

DATES: This AD is effective April 9, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 9, 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 


sroberts on DSK5SPTVN1PROD with RULES
Federal Register / Vol. 79, No. 43 / Wednesday, March 5, 2014 / Rules and Regulations 12369 

and locating Docket No. FAA–2013– 

0866; 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: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6440; 

fax: 425–917–6590; email: 

nancy.marsh@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 all The Boeing Company Model 

737–100, –200, –200C, –300, –400, and 

–500 series airplanes. The NPRM 

published in the Federal Register on 

October 24, 2013 (78 FR 63431). The 

NPRM was prompted by reports of 

cracks found in the aft support fitting, 

the rear spar upper chord, and the rear 

spar web. The NPRM proposed to 

require repetitive inspections for 

cracking of the aft support fitting for the 

MLG beam, and the rear spar upper 

chord and rear spar web in the area of 

RSS 224.14; and repair if necessary. We 

are issuing this AD to detect and correct 

such cracks, which could grow and 

result in a fuel leak and possible fire. 

Comment 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the proposal (78 FR 63431, 

October 24, 2013) and the FAA’s 

response to that comment. 

Statement Regarding Installation of 

Winglets 

Aviation Partners Boeing stated that 

the installation of winglets per 

supplemental type certificate (STC) 

ST01219SE does not affect the 

accomplishment of the manufacturer’s 

service instructions. 

We concur. We have redesignated 

paragraph (c) of the NPRM (78 FR 

63431, October 24, 2013) as paragraph 

(c)(1) in this final rule and added 

paragraph (c)(2) to state that installation 

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

Regulatory_and_Guidance_Library/

rgstc.nsf/0/2C6E3DBDDD36F91C8

62576A4005D64E2?Open

Document&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 

approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

63431, October 24, 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 63431, 

October 24, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 353 

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 ..... Up to 86 work-hours × $85 per 

hour = $7,310 per inspection 

cycle.

$0 Up to $7,310 per inspection cycle Up to $2,580,430 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, 

the FAA amends 14 CFR part 39 as 

follows: 


sroberts on DSK5SPTVN1PROD with RULES
12370 Federal Register / Vol. 79, No. 43 / Wednesday, March 5, 2014 / Rules and Regulations 

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): 

2014–03–06 The Boeing Company: 

Amendment 39–17743; Docket No. 

FAA–2013–0866; Directorate Identifier 

2013–NM–131–AD. 

(a) Effective Date 

This AD is effective April 9, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes, 

certificated in any category. 

(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 

request is not necessary to comply with the 

requirements of 14 CFR 39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

found in the aft support fitting for the main 

landing gear (MLG) beam, and the rear spar 

upper chord and rear spar web. We are 

issuing this AD to detect and correct such 

cracks, which could grow and result in a fuel 

leak and possible fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections: Group 1 

For airplanes identified in Group 1 of 

Boeing Special Attention Service Bulletin 

737–57–1318, dated May 15, 2013: At the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 737–57–1318, dated May 15, 

2013, except as required by paragraph (i) of 

this AD, do inspections and applicable 

corrective actions using a method approved 

in accordance with the procedures specified 

in paragraph (j) of this AD. 

(h) Inspections: Groups 2–7 

For airplanes identified in Groups 2 

through 7 of Boeing Special Attention 

Service Bulletin 737–57–1318, dated May 15, 

2013: At the applicable time specified in 

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

Special Attention Service Bulletin 737–57– 

1318, dated May 15, 2013, except as required 

by paragraph (i) of this AD, do high 

frequency eddy current inspections to detect 

cracking of the aft support fitting for the MLG 

beam, and the rear spar upper chord and rear 

spar web in the area of rear spar station 

224.14, as applicable, in accordance with 

Option 1, 2, or 3 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–57–1318, dated May 15, 

2013. 

(1) If no crack is found, repeat the 

inspection thereafter at the time specified in 

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

Special Attention Service Bulletin 737–57– 

1318, dated May 15, 2013, as applicable. 

Accomplishment of the inspection of the 12 

fastener holes (locations 1–12) in accordance 

with Option 2, Action 3; or Option 3, Action 

3; as specified in note (b) of tables 2 through 

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

Special Attention Service Bulletin 737–57– 

1318, dated May 15, 2013; terminates only 

the corresponding inspections that include 

note (b) in the ‘‘Repeat Interval’’ column of 

the applicable table. 

(2) If any crack is found during any 

inspection required by paragraph (g) or (g)(1) 

of this AD, repair before further flight using 

a method approved in accordance with the 

procedures specified in paragraph (j) of this 

AD. 

(i) Exception to Service Information 

Specifications 

Where Boeing Special Attention Service 

Bulletin 737–57–1318, dated May 15, 2013, 

specifies a compliance time ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(j) 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 

paragraph (k) of this AD. Information may be 

emailed to: 9–ANM-Seattle-ACO–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. 

(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), which 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. 

(k) Related Information 

For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6440; fax: 425–917–6590; 

email: nancy.marsh@faa.gov. 

(l) 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 737–57–1318, dated May 15, 2013. 

(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 January 

18, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–02521 Filed 3–4–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0702; Directorate 

Identifier 2012–NM–181–AD; Amendment 

39–17753; AD 2014–03–15] 

RIN 2120–AA64 

Airworthiness Directives; 328 Support 

Services GmbH (Type Certificate 

Previously Held by AvCraft Aerospace 

GmbH; Fairchild Dornier GmbH; 

Dornier Luftfahrt GmbH) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2008–14– 


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