Federal Register / Vol. 79, No. 159 / Monday, August 18, 2014 / Proposed Rules 48703 

45, PC 12/47 AMM Document No. 02049, 12– 

A–AM–00–00–00–I, revision 28, dated May 

31, 2014, for Models PC–12, PC–12/45, PC– 

12/47, and Data module code 12–B–04–00– 

00–00A–000A–A, ‘‘Structural and 

Component Limitations—Airworthiness 

Limitations,’’ dated March 13, 2014, of the 

Pilatus Model Identification: 12 Aircraft 

Maintenance Manual, PC 12/47E AMM 

Document No. 02300, 12–B–AM–00–00–00– 

I, revision 11, dated May 31, 2014, for Model 

PC–12/47E, into the Limitations section of 

the FAA-approved maintenance program 

(e.g., maintenance manual). These limitations 

section revisions do the following: 

(i) Establish an inspection of the inboard 

flap drive arms, 

(ii) Specify replacement of components 

before or upon reaching the applicable life 

limit, and 

(iii) Specify accomplishment of all 

applicable maintenance tasks within certain 

thresholds and intervals. 

(4) Actions retained from AD 2012–26–16, 

Amendment 39–17311 (78 FR 11572, 

February 19. 2013) for all airplanes: Only 

authorized Pilatus Service Centers can do the 

Supplemental Structural Inspection 

Document (SSID) as required by the 

documents in paragraph (f)(3) of this AD 

because deviations from the type design in 

critical locations could make the airplane 

ineligible for this life extension. 

(5) Actions new to this AD for all airplanes: 

If no compliance time is specified in the 

documents listed in paragraph (f)(3) of this 

AD when doing any corrective actions where 

discrepancies are found as required in 

paragraph (f)(3)(iii) of this AD, do these 

corrective actions before further flight after 

doing the applicable maintenance task. 

(6) Actions new to this AD for all airplanes: 

During the accomplishment of the actions 

required in paragraphs (f)(3)(i), (f)(3)(ii), and 

(f)(3)(iii) of this AD, if a discrepancy is found 

that is not identified in the documents listed 

in paragraph (f)(3) of this AD, before further 

flight after finding the discrepancy, contact 

Pilatus Aircraft LTD, at the address specified 

in paragraph (i) of this AD for a repair 

scheme and incorporate that repair scheme. 

(7) Actions new to this AD for all airplanes: 

Within the next 3 months after the effective 

date of this AD or within the next 150 hours 

TIS after the effective date of this AD, 

whichever occurs first, inspect the inboard 

flap drive arms for cracks and take all 

necessary corrective actions. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

Doug Rudolph, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4059; fax: (816) 329– 

4090; email: doug.rudolph@faa.gov. 

(i) Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(ii) AMOCs approved for AD 2012–26–16, 

Amendment 39–17311 (77 FR 11572, 

February 19, 2013) are not approved as 

AMOCs for 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. 

(h) Special Flight Permit 

Special flight permits are prohibited. 

(i) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No. 2014–0170, dated 

July 17, 2014, for related information. You 

may examine the MCAI on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2014–0594. 

For service information related to this AD, 

contact Pilatus Aircraft LTD., Customer 

Service Manager, CH–6371 STANS, 

Switzerland; telephone: +41 (0) 41 619 33 33; 

fax: +41 (0) 41 619 73 11; Internet: http://

www.pilatus-aircraft.com or email: 

SupportPC12@pilatus-aircraft.com. You may 

review copies of the referenced 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. 

Issued in Kansas City, Missouri, on August 

12, 2014. 

Monica L. Nemecek, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–19490 Filed 8–15–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0570; Directorate 

Identifier 2013–NM–094–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–102, 

–103, –106, –201, –202, –301, –311, and 

–315 airplanes. This proposed AD was 

prompted by fuel system reviews 

conducted by the manufacturer. This 

proposed AD would require revising the 

maintenance or inspection program to 

incorporate new limitations for fuel tank 

systems. We are proposing this AD to 

prevent potential ignition sources 

within the fuel system, which could 

result in a fuel tank explosion. 

DATES: We must receive comments on 

this proposed AD by October 2, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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. 

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– 

0570; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Morton Lee, Propulsion Engineer, 

Propulsion & Services Branch, ANE– 

173; FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone 516–228–7355; fax 

516–794–5531. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
48704 Federal Register / Vol. 79, No. 159 / Monday, August 18, 2014 / Proposed Rules 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0570; Directorate Identifier 

2013–NM–094–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 

Regulation No. 88 (‘‘SFAR 88,’’ 

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 

requires certain type design (i.e., type 

certificate (TC) and supplemental type 

certificate (STC)) holders to substantiate 

that their fuel tank systems can prevent 

ignition sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 

and to develop design changes and 

maintenance procedures if their designs 

do not meet the new fuel tank safety 

standards. As explained in the preamble 

to the rule, we intended to adopt 

airworthiness directives to mandate any 

changes found necessary to address 

unsafe conditions identified as a result 

of these reviews. 

In evaluating these design reviews, we 

have established four criteria intended 

to define the unsafe conditions 

associated with fuel tank systems that 

require corrective actions. The 

percentage of operating time during 

which fuel tanks are exposed to 

flammable conditions is one of these 

criteria. The other three criteria address 

the failure types under evaluation: 

single failures, combination of failures, 

and unacceptable (failure) experience. 

For all three failure criteria, the 

evaluations included consideration of 

previous actions taken that may mitigate 

the need for further action. 

We have determined that the actions 

identified in this proposed AD are 

necessary to reduce the potential of 

ignition sources inside fuel tanks, 

which, in combination with flammable 

fuel vapors, could result in fuel tank 

explosions and consequent loss of the 

airplane. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2007–32R2, 

dated June 27, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model 

DHC–8–102, –103, –106, –201, –202, 

–301, –311, and –315 airplanes. The 

MCAI states: 

Bombardier Aerospace has completed a 

system safety review of the aeroplanes fuel 

system against fuel tank safety standards 

* * *. The identified non-compliances were 

then assessed * * *, to determine if 

mandatory corrective action is required. 

The assessment showed that supplemental 

maintenance tasks are required to prevent 

potential ignition sources within the fuel 

system, which could result in a fuel tank 

explosion. Revisions have been made to Part 

2 ‘‘Airworthiness Limitations List’’ of the 

DHC–8 Maintenance Program Manuals to 

introduce the required maintenance tasks. 

Revision 1 of this [Canadian] AD was 

issued to clarify the phase-in schedule for 

tasks FSL–02 and FSL–17. 

Revision 2 of this [Canadian] AD is issued 

to correct the effective date of AD CF–2013– 

07 [http://www.casa.gov.au/scripts/

nc.dll?WCMS:OLDASSET::svPath=/ADFiles/

over/dhc-8/,svFileName=CF-2013-07.pdf] 

referenced in Part III of the Corrective 

Actions and to clarify the revised phase-in 

schedules in Part II and Part III of the 

Corrective Actions. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0570. 

Relevant Service Information 

Bombardier, Inc. has issued the 

following service information. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

• Bombardier Temporary Revision 

AWL–110, dated August 31, 2007, to 

Part 2, ‘‘Airworthiness Limitations,’’ of 

Bombardier Dash 8 Series 100 

Maintenance Program Manual (MPM), 

Product Support Manual (PSM) 1–8–7. 

• Bombardier Temporary Revision 

AWL 2–43, dated August 31, 2007, to 

Part 2, ‘‘Airworthiness Limitations,’’ of 

Bombardier Dash 8 Series 200 MPM, 

PSM 1–82–7. 

• Bombardier Temporary Revision 

AWL 3–109, dated August 31, 2007, to 

Part 2, ‘‘Airworthiness Limitations,’’ of 

Bombardier Dash 8 Series 300 MPM, 

PSM 1–83–7. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

This proposed AD would require 

revisions to certain operator 

maintenance documents to include new 

actions (e.g., inspections) and/or Critical 

Design Configuration Control 

Limitations (CDCCLs). Compliance with 

these actions and/or CDCCLs is required 

by 14 CFR 91.403(c). For airplanes that 

have been previously modified, altered, 

or repaired in the areas addressed by 

this proposed AD, the operator may not 

be able to accomplish the actions 

described in the revisions. In this 

situation, to comply with 14 CFR 

91.403(c), the operator must request 

approval for an alternative method of 

compliance according to paragraph (j)(1) 

of this proposed AD. The request should 

include a description of changes to the 

required inspections that will ensure the 

continued operational safety of the 

airplane. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This Proposed AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 159 / Monday, August 18, 2014 / Proposed Rules 48705 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In an NPRM having Directorate 

Identifier 2012–NM–101–AD (78 FR 

78285, December 26, 2013), we 

proposed to prevent the use of repairs 

that were not specifically developed to 

correct the unsafe condition, by 

requiring that the repair approval 

provided by the State of Design 

Authority or its delegated agent 

specifically refer to the FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, we proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

proposed AD. 

One commenter to the NPRM having 

Directorate Identifier 2012–NM–101–AD 

(78 FR 78285, December 26, 2013) stated 

the following: ‘‘The proposed wording, 

being specific to repairs, eliminates the 

interpretation that Airbus messages are 

acceptable for approving minor 

deviations (corrective actions) needed 

during accomplishment of an AD 

mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed the 

paragraph and retitled it ‘‘Contacting the 

Manufacturer.’’ This paragraph now 

clarifies that for any requirement in this 

proposed AD to obtain corrective 

actions from a manufacturer, the actions 

must be accomplished using a method 

approved by the FAA, or Transport 

Canada Civil Aviation (TCCA), or 

Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DAO, the approval must include 

the DAO-authorized signature. The DAO 

signature indicates that the data and 

information contained in the document 

are TCCA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DAO-authorized signature approval are 

not TCCA-approved, unless TCCA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

Costs of Compliance 

We estimate that this proposed AD 

affects 122 airplanes of U.S. registry. 

We also estimate that it would take 

about 1 work-hour per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $10,370, or $85 per product. 

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 proposed 

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 determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Bombardier, Inc.: Docket No. FAA–2014– 

0570; Directorate Identifier 2013–NM– 

094–AD. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
48706 Federal Register / Vol. 79, No. 159 / Monday, August 18, 2014 / Proposed Rules 

(a) Comments Due Date 

We must receive comments by October 2, 

2014. 

(b) Affected ADs 

This AD affects AD 2008–13–09, 

Amendment 39–15572 (73 FR 47029, August 

13, 2008). 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–102, –103, –106, –201, –202, –301, 

–311, and –315 airplanes, certificated in any 

category, serial numbers (S/N) 003 through 

624 inclusive, and 626. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to prevent potential 

ignition sources within the fuel system, 

which could result in a fuel tank explosion. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Maintenance or Inspection Program 

Revision 

Within 30 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to include fuel 

system limitation (FSL) Task Numbers FSL– 

02 and FSL–17, as specified in the applicable 

temporary revision (TR) identified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD. 

The initial compliance times for 

accomplishing the tasks are specified in 

paragraphs (h)(1), (h)(2), and (h)(3) of this 

AD. Doing this revision terminates the 

requirements of paragraph (f) of AD 2008– 

13–09, Amendment 39–15572 (73 FR 47029, 

August 13, 2008), for Task Numbers FSL–02 

and FSL–17 only. 

(1) Bombardier TR AWL–110, dated 

August 31, 2007, to Part 2, ‘‘Airworthiness 

Limitations,’’ of Bombardier Dash 8 Series 

100 Maintenance Program Manual (MPM), 

Product Support Manual (PSM) 1–8–7. 

(2) Bombardier TR AWL 2–43, dated 

August 31, 2007, to Part 2, ‘‘Airworthiness 

Limitations,’’ of Bombardier Dash 8 Series 

200 MPM, PSM 1–82–7. 

(3) Bombardier TR AWL 3–109, dated 

August 31, 2007, to Part 2, ‘‘Airworthiness 

Limitations,’’ of Bombardier Dash 8 Series 

300 MPM, PSM 1–83–7. 

(h) Phase-in Compliance Times 

For airplanes having S/Ns 003 through 624, 

and S/N 626, the initial compliance times are 

specified in paragraphs (h)(1), (h)(2), and 

(h)(3) of this AD, as applicable. 

(1) For airplanes having S/Ns 003 through 

624 on which the applicable modification 

summaries (ModSums) specified in 

paragraphs (h)(1)(i), (h)(1)(ii), and (h)(1)(iii) 

of this AD have been incorporated before the 

effective date of this AD: The compliance 

time for the initial inspection in FSL Task 

Number FSL–02 and the initial functional 

check in FSL Task Number FSL–17 is within 

6,000 flight hours or 36 months after the 

effective date of this AD, whichever occurs 

first. Airplane configurations can be a 

combination of the configurations specified 

in paragraphs (h)(1)(i), (h)(1)(ii), and 

(h)(1)(iii) of this AD. 

(i) For airplanes having S/Ns 003 through 

624: Bombardier ModSum Package 

8Q101512, Revision G, dated June 10, 2009; 

and Bombardier ModSum Package 

8Q101865, Revision B, dated May 26, 2008. 

(ii) For airplanes having S/Ns 003 through 

624 with auxiliary power unit (APU) option: 

Bombardier ModSum Package 8Q902144, 

Revision E, dated June 17, 2009. 

(iii) For airplanes having S/Ns 003 through 

624 with a long-range fuel system installed: 

Bombardier ModSum Package 8Q902091, 

Revision C, dated December 22, 2006. 

(2) For airplanes having S/Ns 003 through 

624 on which the applicable ModSum 

packages specified in paragraphs (h)(1)(i), 

(h)(1)(ii), and (h)(1)(iii) of this AD have not 

been incorporated before the effective date of 

this AD: The compliance time for the initial 

inspection in FSL Task Number FSL–02 and 

the initial functional check in FSL Task 

Number FSL–17 is before further flight after 

incorporation of all applicable ModSum 

packages specified in paragraphs (h)(1)(i), 

(h)(1)(ii), and (h)(1)(iii) of this AD. Airplane 

configurations can be a combination of the 

configurations specified in paragraphs 

(h)(1)(i), (h)(1)(ii), and (h)(1)(iii) of this AD. 

(3) For the airplane having serial number 

626: The initial compliance time is at the 

applicable time specified in paragraph 

(h)(3)(i) or (h)(3)(ii) of this AD. 

(i) If Bombardier ModSum Package 

8Q902091, Revision C, dated December 22, 

2006, has been incorporated before the 

effective date of this AD: The compliance 

time for doing the initial inspection specified 

in FSL Task Number FSL–02 and the initial 

functional check specified in FSL Task 

Number FSL–17 is within 6,000 flight hours 

or within 36 months after the effective date 

of this AD, whichever occurs first. 

(ii) If Bombardier ModSum Package 

8Q902091 Revision C, dated December 22, 

2006, has not been incorporated before the 

effective date of this AD: The compliance 

time for doing the initial inspection in FSL 

Task Number FSL–02 and the initial 

functional check in FSL Task Number FSL– 

17 is before further flight after incorporation 

of Bombardier ModSum Package 8Q901091. 

(i) No Alternative Actions, Intervals, and/or 

Critical Design Configuration Control 

Limitations (CDCCLs) 

After accomplishing the revision required 

by paragraph (g) of this AD, no alternative 

actions (e.g., inspections), intervals, and/or 

CDCCLs may be used unless the actions, 

intervals, and/or CDCCLs are approved as an 

alternative method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (j) 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) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

Transport Canada Civil Aviation (TCCA), or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2007–32R2, 

dated June 27, 2013, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2014–0570. 

(2) 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. 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. 

Issued in Renton, Washington, on August 

7, 2014. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–19552 Filed 8–15–14; 8:45 am] 

BILLING CODE 4910–13–P 


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