Federal Register / Vol. 79, No. 71 / Monday, April 14, 2014 / Proposed Rules 20829 

the effective date of this AD or within the 

next 114 months after the effective date of 

this AD, whichever occurs first, modify the 

aft main spar in the cabin area following the 

INSTRUCTIONS section of Diamond Aircraft 

Industries GmbH Work Instructions WI–MSB 

40–074, WI–MSB D4–094, and WI–MSB F4– 

028 (co-published as a single document), 

dated May 10, 2013, as specified in Diamond 

Aircraft Industries GmbH Mandatory Service 

Bulletins (MSB) 40–074, D4–094, and F4–028 

(co-published as a single document), dated 

May 10, 2013. 

(3) For airplanes with 2,000 hours or more 

than 2,000 hours TIS but less than 2,500 

hours TIS: At or before 500 hours TIS after 

the effective date of this AD or within the 

next 48 months after the effective date of this 

AD, whichever occurs first, modify the aft 

main spar in the cabin area following the 

INSTRUCTIONS section of Diamond Aircraft 

Industries GmbH Work Instructions WI–MSB 

40–074, WI–MSB D4–094, and WI–MSB F4– 

028 (co-published as a single document), 

dated May 10, 2013, as specified in Diamond 

Aircraft Industries GmbH Mandatory Service 

Bulletins (MSB) 40–074, D4–094, and F4–028 

(co-published as a single document), dated 

May 10, 2013. 

(4) For airplanes with 2,500 hours or more 

than 2,500 hours TIS: Within the next 100 

hours TIS after the effective date of this AD 

or within the next 12 months after the 

effective date of this AD, whichever occurs 

first, inspect the aft spar center section 

following DIAMOND AIRCRAFT 

INDUSTRIES DA 40 SERIES AIRPLANE 

MAINTENANCE MANUAL (AMM), Chapter 

Section 05–28–50, Section 2 (Cockpit), Item 

31, sub-item ‘‘The rear main bulkhead,’’ page 

11, Rev. 7, dated April 1, 2013, and perform 

any applicable corrective actions. 

(i) After doing the inspection required by 

paragraph (f)(4) of this AD including any 

applicable corrective actions, at or before 500 

hours TIS after the effective date of this AD 

or within the next 48 months after the 

effective date of this AD, whichever occurs 

first, modify the aft main spar in the cabin 

area following the INSTRUCTIONS section of 

Diamond Aircraft Industries GmbH Work 

Instructions WI–MSB 40–074, WI–MSB D4– 

094, and WI–MSB F4–028 (co-published as a 

single document), dated May 10, 2013, as 

specified in Diamond Aircraft Industries 

GmbH Mandatory Service Bulletins (MSB) 

40–074, D4–094, and F4–028 (co-published 

as a single document), dated May 10, 2013. 

(ii) The modification required in paragraph 

(f)(4)(i) of this AD may be done instead of the 

inspection required by paragraph (f)(4) of this 

AD provided it is done within the next 100 

hours TIS after the effective date of this AD 

or within the next 12 months after the 

effective date of this AD, whichever occurs 

first. 

(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 

ATTN: Mike Kiesov, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4144; fax: (816) 329– 

4090; email: mike.kiesov@faa.gov. 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. 

(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) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No.: 2013–0145, dated 

July 15, 2013, for related information. You 

may examine the MCAI on the Internet at 

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

and locating Docket No. FAA–2014–0226. 

For service information related to this AD, 

contact Diamond Aircraft Industries GmbH, 

N.A. Otto-Str.5, A–2700 Wiener Neustadt, 

Austria; telephone: +43 2622 26700; fax: +43 

2622 26780; email: office@diamond-air.at; 

Internet: http://www.diamondaircraft.com/

contact/technical.php. 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 April 

8, 2014. 

Timothy Smyth, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–08312 Filed 4–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0196; Directorate 

Identifier 2014–NM–015–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 CL–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes, Model CL–600–2D15 

(Regional Jet Series 705) airplanes, 

Model CL–600–2D24 (Regional Jet 

Series 900) airplanes, and Model CL– 

600–2E25 (Regional Jet Series 1000) 

airplanes. This proposed AD was 

prompted by two in-service reports of 

fracture of the rudder pedal tubes 

installed on the pilot-side rudder bar 

assembly. This proposed AD would 

require repetitive inspections for 

cracking and damage of the pilot-side 

rudder pedal tubes, and corrective 

action if necessary. This proposed AD 

would also provide optional terminating 

action for the repetitive inspections. We 

are proposing this AD to detect and 

correct cracked and damaged pilot-side 

rudder pedal tubes, which could result 

in loss of function of the pilot’s rudder 

pedal during flight, takeoff, or landing, 

and could result in reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 29, 2014. 

ADDRESSES: You may send comments 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., 400 Coˆte-Vertu Road West, Dorval, 

Que ́bec H4S 1Y9, Canada; telephone 

514–855–5000; fax 514–855–7401; email 

thd.crj@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– 

0196; 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 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

20830 Federal Register / Vol. 79, No. 71 / Monday, April 14, 2014 / Proposed Rules 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; fax (516) 794–5531. 

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–2014–0196; Directorate Identifier 

2014–NM–015–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 

Transport Canada Civil Aviation 

(TCCA), which is the airworthiness 

authority for Canada, has issued 

Canadian Airworthiness Directive CF– 

2014–02, dated January 8, 2014 (referred 

to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for certain Bombardier, Inc. 

Model CL–600–2C10 (Regional Jet 

Series 700, 701, & 702) airplanes, Model 

CL–600–2D15 (Regional Jet Series 705) 

airplanes, Model CL–600–2D24 

(Regional Jet Series 900) airplanes, and 

Model CL–600–2E25 (Regional Jet Series 

1000) airplanes. The MCAI states: 

There have been two in-service reports of 

fracture of the rudder pedal tubes installed 

on the pilot-side rudder bar assembly on CL– 

600–2B19 model aeroplanes. 

Laboratory examination of the fractured 

rudder pedal tubes found that in both cases, 

the fatigue cracks initiated at the aft taper pin 

holes where the connecting rod fitting is 

attached. Fatigue testing of the rudder pedal 

tubes confirmed that the fatigue cracking is 

due to loads induced during parking brake 

application. Therefore, only the rudder pedal 

tubes on the pilot’s side are vulnerable to 

fatigue cracking as the parking brake is 

primarily applied by the pilot. 

Loss of pilot rudder pedal input during 

flight would result in reduced yaw 

controllability of the aeroplane. Loss of pilot 

rudder pedal input during takeoff or landing 

may lead to a runway excursion. 

Although there have been no reported 

failures to date on any CL–600–2C10, –2D15, 

–2D24, and –2D25 model aeroplanes, the 

same torque tubes part number (P/N) 600– 

90204–3 are installed, which may be prone 

to premature fatigue cracking. 

This [Canadian] AD mandates initial and 

repetitive [detailed and eddy current] 

inspections [for cracking and damage] of the 

pilot-side rudder pedal tubes, P/N 600– 

90204–3, until the terminating action 

[replacement of both pilot-side rudder bar 

assemblies] is accomplished [and corrective 

actions if necessary]. 

Corrective actions include 

replacement of the rudder bar assembly 

and repair. 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– 

0196. 

Relevant Service Information 

Bombardier has issued Service 

Bulletin 670BA–27–065, dated 

November 15, 2013. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

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. 

Repair Approvals 

In many FAA transport ADs, when 

the service information specifies to 

contact the manufacturer for further 

instructions if certain discrepancies are 

found, we typically include in the AD 

a requirement to accomplish the action 

using a method approved by either the 

FAA or the State of Design Authority (or 

its delegated agent). 

We have recently been notified that 

certain laws in other countries do not 

allow such delegation of authority, but 

some countries do recognize design 

approval organizations. In addition, we 

have become aware that some U.S. 

operators have used repair instructions 

that were previously approved by a 

State of Design Authority or a Design 

Approval Holder (DAH) as a method of 

compliance with this provision in FAA 

ADs. Frequently, in these cases, the 

previously approved repair instructions 

come from the airplane structural repair 

manual or the DAH repair approval 

statements that were not specifically 

developed to address the unsafe 

condition corrected by the AD. Using 

repair instructions that were not 

specifically approved for a particular 

AD creates the potential for doing 

repairs that were not developed to 

address the unsafe condition identified 

by the MCAI AD, the FAA AD, or the 

applicable service information, which 

could result in the unsafe condition not 

being fully corrected. 

To prevent the use of repairs that 

were not specifically developed to 

correct the unsafe condition, certain 

requirements of this proposed AD 

would require that the repair approval 

specifically refer to the FAA AD. This 

change is 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 use the phrase ‘‘its 

delegated agent, or the DAH with State 

of Design Authority design organization 

approval, as applicable’’ in this 

proposed AD to refer to a DAH 

authorized to approve certain required 

repairs for this proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 400 airplanes of U.S. registry. 

We also estimate that it would take 

about 3 work-hours per product to 

comply with the basic inspection 

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 $102,000, or $255 per 

airplane, per inspection cycle. 

In addition, we estimate that any 

necessary replacement of the rudder 

pedal tubes would take about 6 workhours and require parts costing $2,850, 

for a cost of $3,360 per product. We 

have no way of determining the number 

of aircraft that might need this action. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition repairs 

specified in this proposed 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. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 79, No. 71 / Monday, April 14, 2014 / Proposed Rules 20831 

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 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. Amend § 39.13 by adding the 

following new airworthiness directive 

(AD): 

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

0196; Directorate Identifier 2014–NM– 

015–AD. 

(a) Comments Due Date 

We must receive comments by May 29, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1), (c)(2), and (c)(3) of this 

AD, certificated in any category. 

(1) Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes, serial numbers 10002 through 

10342 inclusive. 

(2) Bombardier, Inc. Model CL–600–2D15 

(Regional Jet Series 705), and Model CL–600– 

2D24 (Regional Jet Series 900) airplanes, 

serial numbers 15001 through 15337 

inclusive. 

(3) Bombardier, Inc. Model CL–600–2E25 

(Regional Jet Series 1000) airplanes, serial 

numbers 19001 through 19040 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by two in-service 

reports of fracture of the rudder pedal tubes 

installed on the pilot-side rudder bar 

assembly. We are issuing this AD to detect 

and correct cracked and damaged pilot-side 

rudder pedal tubes, which could result in 

loss of function of the pilot’s rudder pedal 

during flight, takeoff, or landing, and could 

result in reduced controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Before the accumulation of 26,000 total 

flight cycles or within 3 months after the 

effective date of this AD, whichever occurs 

later: Perform a detailed or eddy current 

inspection for cracking around the aft tapered 

holes of both pilot-side rudder pedal tubes 

and for damage of the rudder pedal tubes in 

locations other than around the aft tapered 

holes, in accordance with Part A of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–27–065, dated 

November 15, 2013. Repeat the inspection 

thereafter at the applicable intervals specified 

in paragraph (g)(1) or (g)(2) of this AD, until 

the terminating action specified in paragraph 

(i) of this AD is done. 

(1) If the most recent inspection was a 

detailed inspection: Within 750 flight cycles 

after doing the detailed inspection. 

(2) If the most recent inspection was a eddy 

current inspection: Within 1,250 flight cycles 

after doing the eddy current inspection. 

(h) Corrective Actions 

(1) If any crack is found around the aft 

tapered holes during any inspection required 

by paragraph (g) of this AD, before further 

flight, replace the rudder bar assembly, in 

accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–27–065, dated 

November 15, 2013. 

(2) If any damage is found during any 

inspection required by paragraph (g) of this 

AD in a location other than around the aft 

tapered holes: Before further flight, repair 

using a method approved by the Manager, 

New York ACO; or TCCA (or its delegated 

agent, or the Design Approval Holder (DAH) 

with TCCA design organization approval, as 

applicable). For a repair method to be 

approved, the repair approval must 

specifically refer to this AD. 

(i) Optional Terminating Action 

Replacement of both pilot-side rudder bar 

assemblies, in accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–27–065, dated 

November 15, 2013, constitutes terminating 

action for the repetitive inspections required 

by paragraph (g) 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. Send information to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

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, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the DAH with a State 

of Design Authority’s design organization 

approval, as applicable). You are required to 

ensure 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–2014–02, dated 

January 8, 2014, 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– 

2014–0196. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

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. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

20832 Federal Register / Vol. 79, No. 71 / Monday, April 14, 2014 / Proposed Rules 

Issued in Renton, Washington, on April 4, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–08304 Filed 4–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0241; Directorate 

Identifier 2014–CE–008–AD] 

RIN 2120–AA64 

Airworthiness Directives; British 

Aerospace Regional Aircraft Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

British Aerospace Regional Aircraft 

Jetstream Model 3201 airplanes that 

would supersede AD 2007–10–16. This 

proposed AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as the need to 

incorporate revisions to the 

Airworthiness Limitations section of the 

Instructions for Continued 

Airworthiness. We are issuing this 

proposed AD to require actions to 

address the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by May 29, 2014. 

ADDRESSES: You may send comments 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 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact BAE Systems 

(Operations) Limited, Customer 

Information Department, Prestwick 

International Airport, Ayrshire, KA9 

2RW, Scotland, United Kingdom; 

telephone: +44 1292 675207; fax: +44 

1292 675704; email: RApublications@

baesystems.com; Internet: http://

www.baesystems.com/Businesses/

RegionalAircraft/. 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. 

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– 

0241; 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 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: 

Taylor Martin, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4138; fax: (816) 329–4090; email: 

taylor.martin@faa.gov. 

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–2014–0241; Directorate Identifier 

2014–CE–008–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 because of those 

comments. 

We will post all comments we 

receive, without change, to http://

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 

On May 9, 2007, we issued AD 2007– 

10–16, Amendment 39–15057 (72 FR 

27953, May 18, 2007). That AD required 

actions intended to address an unsafe 

condition on all British Aerospace 

Regional Aircraft Jetstream Model 3201 

airplanes and was based on mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country. 

Since we issued AD 2007–10–16, 

Amendment 39–15057 (72 FR 27953, 

May 18, 2007), BAE Systems 

(Operations) Ltd amended Jetstream 

Series 3200 Aircraft Maintenance 

Manual (AMM) Chapter 05–10–05, 

Airworthiness Limitations. Some life 

limits have been amended and new life 

limits introduced. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD No.: 2014– 

0044, dated February 24, 2014 (referred 

to after this as ‘‘the MCAI’’), to correct 

an unsafe condition for the specified 

products. The MCAI states: 

The Jetstream Series 3200 Aircraft 

Maintenance Manual (AMM), includes 

Chapter 05–10–05 ‘‘Airworthiness 

Limitations, Description and Operation’’. The 

maintenance tasks and limitations contained 

in this chapter have been identified as 

mandatory actions for continued 

airworthiness and EASA issued AD 2007– 

0074 to require operators to comply with 

those instructions. 

Since that AD was issued, BAE Systems 

(Operations) Ltd amended Jetstream Series 

3200 AMM Chapter 05–10–05 to introduce 

life limitations for the main landing gear 

radius rod mounting shaft assemblies and to 

incorporate wing structure inspections 

previously introduced through BAE Systems 

(Operations) Ltd Service Bulletin (SB) SB 51– 

JA020940. In addition, a new table was 

introduced to provide extended fatigue life 

limitations for structural items for aeroplanes 

entered into a life extension programme. 

Reference to BAE Systems (Operations) Ltd 

SB 32–JA981042 was updated from Revision 

7 to Revision 8 to reflect increased life limits 

of the nose landing gear. 

Failure to comply with the new and more 

restrictive instructions could result in an 

unsafe condition. 

For the reasons described above, this EASA 

AD retains the requirements of EASA AD 

2007–0074, which is superseded, and 

requires implementation of the maintenance 

requirements and/or airworthiness 

limitations as specified in Chapter 05–10–05 

of the Jetstream Series 3200 AMM at Revision 

29. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2014–0241. 

Relevant Service Information 

BAE Systems (Operations) Ltd has 

issued British Aerospace Jetstream 3200 

Series Aircraft Maintenance Manual, 

Revision 29, dated December 15, 2012. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS