28128 Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Rules and Regulations 

(ii) For airplanes with 7,500 through 9,999 

hours TIS, inspect within the next 60 days 

after the effective date of this AD. 

(iii) For airplanes with 5,000 through 7,499 

hours TIS, inspect within the next 6 months 

after the effective date of this AD. 

(iv) For airplanes with less than 5,000 

hours TIS, inspect when the airplane 

accumulates a total of 5,000 hours TIS or 

within the next 12 months after the effective 

date of this AD, whichever occurs later. 

(h) Repair 

If any damage, cracks, and/or cracks that 

exceed the allowable limits specified in the 

service bulletin are found during the 

inspection required in paragraph (g)(1) of this 

AD, before further flight, repair or replace 

parts as necessary following Twin 

Commander Aircraft LLC Service Bulletin 

241, dated, September 26, 2012. If Twin 

Commander Aircraft LLC Service Bulletin 

241, dated, September 26, 2012, does not give 

procedures for repair of the damaged area, 

before further flight, you must contact Twin 

Commander Aircraft LLC to obtain repair 

instructions approved by the Seattle Aircraft 

Certification Office (ACO) specifically for 

compliance with this AD and incorporate 

those instructions. You can find contact 

information for Twin Commander Aircraft 

LLC in paragraph (l)(2) of this AD. 

(i) Modification and Reassembly 

(1) Before further flight after completing 

the actions in paragraphs (g) and (h) of this 

AD, modify and reassemble the airplane 

using the modification and reassembly 

procedures in Part II of Twin Commander 

Aircraft LLC Service Bulletin 241, dated, 

September 26, 2012. 

(2) Although Twin Commander Aircraft 

LLC Service Bulletin 241, dated September 

26, 2012, states that at least one person on 

the modification team must have completed 

the Twin Commander Aircraft LLC approved 

training, the FAA does not require that a 

mechanic complete this specialized training 

to do the modification work required in this 

AD. Regulations 14 CFR 65.81(a) and 14 CFR 

65.81(b) provide criteria about qualifications 

of those performing maintenance; in this 

case, the requirements 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 the 

Related Information section 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. 

(k) Related Information 

For more information about this AD, 

contact Vince Massey, Aerospace Engineer, 

FAA, Seattle ACO, 1601 Lind Avenue SW., 

Renton, WA 98057; telephone: (425) 917– 

6475; fax: (425) 917–6590; email: 

vince.massey@faa.gov. 

(l) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51: 

(i) Twin Commander Aircraft LLC Service 

Bulletin 241, dated September 26, 2012. 

(ii) Reserved. 

(2) For service information identified in 

this AD, contact Twin Commander Aircraft 

LLC; 1176 Telecom Drive, Creedmoor, NC 

27522; telephone: (360) 403–0258; email: 

gpence@twincommander.com; Internet: 

http://www.twincommander.com. 

(3) You may review copies of the service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, call 

(816) 329–4148. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr_locations.html. 

Issued in Kansas City, Missouri, on April 

25, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–10498 Filed 5–13–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0614; Directorate 

Identifier 2007–NM–351–AD; Amendment 

39–17450; AD 2013–09–08] 

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 737–300, –400, 

and –500 series airplanes. This AD was 

prompted by reports of two in-service 

occurrences on Model 737–400 

airplanes of total loss of boost pump 

pressure of the fuel feed system, 

followed by loss of fuel system suction 

feed capability on one engine, and inflight shutdown of the engine. This AD 

requires repetitive operational tests of 

the engine fuel suction feed of the fuel 

system, and corrective actions if 

necessary. We are issuing this AD to 

detect and correct loss of the engine fuel 

suction feed capability of the fuel 

system, which, in the event of total loss 

of the fuel boost pumps, could result in 

dual engine flameout, inability to restart 

the engines, and consequent forced 

landing of the airplane. 

DATES: This AD is effective June 18, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of June 18, 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, Washington. 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: Sue 

Lucier, Aerospace Engineer, Propulsion 

Branch, ANM–140S, Seattle Aircraft 

Certification Office, FAA, 1601 Lind 

Avenue SW., Renton, Washington 

98057–3356; phone: 425–917–6438; fax: 

425–917–6590; email: 

suzanne.lucier@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to include an AD 

that would apply to the specified 

products. That SNPRM published in the 

Federal Register on January 30, 2013 

(78 FR 6254). The original NPRM (73 FR 

32258, June 6, 2008) proposed to require 

repetitive operational tests of the engine 


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Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Rules and Regulations 28129 

fuel suction feed of the fuel system, and 

other related testing if necessary. That 

SNPRM revised the NPRM by proposing 

to require repetitive operational tests 

and corrective actions if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM 

(78 FR 6254, January 30, 2013) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 827 

airplanes of U.S. registry. We estimate 

the following costs to comply with this 

AD: 

ESTIMATED COSTS

Action Labor cost Cost per product Cost on U.S. 

operators 

Operational Test ........ Up to 12 work-hours × $85 per hour = $1,020 per engine, per test ...... Up to $2,040 ............. Up to $1,687,080. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the 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): 

2013–09–08 the Boeing Company: 

Amendment 39–17450; Docket No. 

FAA–2008–0614; Directorate Identifier 

2007–NM–351–AD. 

(a) Effective Date 

This AD is effective June 18, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 737–300, –400, and –500 

series airplanes, certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 2800, Aircraft Fuel System. 

(e) Unsafe Condition 

This AD was prompted by reports of two 

in-service occurrences on Model 737–400 

airplanes of total loss of boost pump pressure 

of the fuel feed system, followed by loss of 

fuel system suction feed capability on one 

engine, and in-flight shutdown of the engine. 

We are issuing this AD to detect and correct 

loss of the engine fuel suction feed capability 

of the fuel system, which in the event of total 

loss of the fuel boost pumps could result in 

dual engine flameout, inability to restart the 

engines, and consequent forced landing of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Operational Test and Corrective Actions 

Within 7,500 flight hours or 24 months 

after the effective date of this AD, whichever 

occurs first: Perform an operational test of the 

engine fuel suction feed of the fuel system, 

and do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–28A1407, dated May 14, 2012. Do all 

applicable corrective actions before further 

flight. Repeat the operational test thereafter at 

intervals not to exceed 7,500 flight hours or 

24 months, whichever occurs first. 

Thereafter, except as provided in paragraph 

(h) of this AD, no alternative procedures or 

repetitive test intervals are allowed. 

(h) 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. 

(i) Related Information 

For more information about this AD, 

contact Sue Lucier, Aerospace Engineer, 

Propulsion Branch, ANM–140S, Seattle 

Aircraft Certification Office, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6438; fax: 425–917– 

6590; email: suzanne.lucier@faa.gov. 


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28130 Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Rules and Regulations 

(j) 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 737– 

28A1407, dated May 14, 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 review copies of the 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, Washington. 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 April 24, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–10657 Filed 5–13–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1072; Directorate 

Identifier 2012–NM–141–AD; Amendment 

39–17449; AD 2013–09–07] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2B19 

(Regional Jet Series 100 & 440) 

airplanes. This AD was prompted by 

reports of two in-service incidents 

where the left main landing gear (MLG) 

failed to extend. This AD requires 

installing stopper plates on the aft 

uplock frames in the MLG bay adjacent 

to the right and left MLG uplock 

assemblies. We are issuing this AD to 

prevent incorrect installation of the 

upper bolt in the MLG uplock assembly, 

which could prevent the MLG from 

extending and could adversely affect the 

safe landing of the airplane. 

DATES: This AD becomes effective June 

18, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 18, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office (ACO), 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; phone: 516–228–7328; 

fax: 516–794–5531. 

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. That 

NPRM was published in the Federal 

Register on October 16, 2012 (77 FR 

63281). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information (MCAI) 

states: 

There have been two reported in-service 

incidents where the left main landing gear 

(MLG) failed to extend. The investigation 

revealed that in both cases, the uplock 

assembly had been replaced prior to the inservice incidents and the upper bolt of the 

uplock assembly was incorrectly installed. 

The incorrect installation of the upper bolt 

resulted in the uplock assembly pivoting on 

the lower attachment bolt and preventing the 

MLG from extending under normal or 

alternate extension. 

The potential for an incorrect installation 

of the upper bolt could occur at both the left 

hand side (LHS) and/or the right hand side 

(RHS) MLG uplock assembly. Failure of the 

MLG to extend could adversely affect the safe 

landing of the aeroplane. 

This [Canadian] AD mandates the 

installation of stopper plates on the aft 

uplock frames in the MLG bay, adjacent to 

both the RHS and LHS MLG uplock 

assemblies, to prevent an incorrect 

installation of the MLG uplock assembly. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Actions Since the NPRM (77 FR 63281, 

October 16, 2012) Was Issued 

We have reviewed Bombardier 

Service Bulletin 601R–32–109, Revision 

A, dated February 26, 2013. In the 

NPRM (77 FR 63281, October 16, 2012), 

we referred to Bombardier Service 

Bulletin 601R–32–109, dated May 29, 

2012, as the appropriate source of 

service information for doing the actions 

specified in the NPRM. Revision A of 

the service information adds 

information for parts that are listed in 

paragraph 1.G. ‘‘Material—Price and 

Availability,’’ and small editorial 

changes that do not have an effect on 

the technical content of the service 

information. 

We have updated paragraphs (g) and 

(j) of this AD to refer to Bombardier 

Service Bulletin 601R–32–109, Revision 

A, dated February 26, 2013. We have 

also added a new paragraph (h) to this 

AD to give credit for actions done before 

the effective date of this AD, using 

Bombardier Service Bulletin 601R–32– 

109, dated May 29, 2012, and reidentified the subsequent paragraph 

identifiers accordingly. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

The National Transportation Safety 

Board supported the NPRM (77 FR 

63281, October 16, 2012). 

Request To Shorten the Compliance 

Time 

The Air Line Pilots Association 

International (ALPA) requested that the 

proposed compliance time in the NPRM 

(77 FR 63281, October 16, 2012) be 

shortened from ‘‘Within 5,500 flight 

hours or 48 months after the effective 

date of this AD, whichever occurs first 

. . . .’’ to ‘‘Within 2,400 flight hours or 

24 months after the effective date of the 

AD, whichever occurs first . . . .’’ The 

ALPA based its suggested compliance 

time on the two reported in-service 

incidents and the potential safety 

implication of landing with an MLG 

fully or partially retracted. 

We do not agree with the request to 

shorten the compliance time. The 

proposed compliance time in the NPRM 

(77 FR 63281, October 16, 2012) was 

based on a risk assessment completed 

by the airplane manufacturer, 

Bombardier, Inc. The risk was 

conservatively assessed with a 

compliance time of 6,000 flight hours, 

based on the estimated release date of 

Bombardier service information. 

Transport Canada Civil Aviation 

(TCCA), the State of Design Authority, 


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