Federal Register / Vol. 79, No. 178 / Monday, September 15, 2014 / Proposed Rules 54919 

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): 

Dassault Aviation: Docket No. FAA–2014– 

0626; Directorate Identifier 2014–NM– 

017–AD. 

(a) Comments Due Date 

We must receive comments by October 30, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Dassault Aviation 

Model FAN JET FALCON and FAN JET 

FALCON SERIES C, D, E, F, and G airplanes, 

certificated in any category, all serial 

numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Time Limits and 

Maintenance Checks. 

(e) Reason 

This AD was prompted by our 

determination of the need for a revision to 

the airplane airworthiness limitations to 

introduce changes to the maintenance 

requirements and airworthiness limitations. 

We are issuing this AD to prevent reduced 

structural integrity of the airplane. 

(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 incorporate the 

information specified in Chapter 5–40, 

Airworthiness Limitations, DGT 131028, 

Revision 15, dated March 2012, of the 

Dassault Aviation Falcon 20 Maintenance 

Manual. The initial compliance time for 

accomplishing the actions specified in 

Chapter 5–40, Airworthiness Limitations, 

DGT 131028, Revision 15, dated March 2012, 

of the Dassault Aviation Falcon 20 

Maintenance Manual is at the applicable time 

specified in Chapter 5–40, Airworthiness 

Limitations, DGT 131028, Revision 15, dated 

March 2012, of the Dassault Aviation Falcon 

20 Maintenance Manual, or within 60 days 

after the effective date of this AD, whichever 

occurs later. Where the threshold column in 

the table in paragraph B, Mandatory 

Maintenance Operations, of Chapter 5–40, 

Airworthiness Limitations, DGT 131028, 

Revision 15, dated March 2012, of the 

Dassault Aviation Falcon 20 Maintenance 

Manual specifies a compliance time in flight 

hours, those compliance times are total flight 

hours. Where the threshold column in the 

table in paragraph B, Mandatory 

Maintenance Operations, of Chapter 5–40, 

Airworthiness Limitations, DGT 131028, 

Revision 15, dated March 2012, of the 

Dassault Aviation Falcon 20 Maintenance 

Manual specifies a compliance time in years, 

those compliance times are since the date of 

issuance of the original French or EASA 

standard airworthiness certificate or date of 

issuance of the original French or EASA 

export certificate of airworthiness. 

(h) No Alternative Actions and Intervals 

After accomplishing the revision required 

by paragraph (g) of this AD, 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 (i)(1) of 

this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; fax 425–227–1149. 

Information may be emailed to: 9–ANM–116– 

AMOC–REQUESTS@faa.gov. 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 

the European Aviation Safety Agency 

(EASA); or Dassault Aviation’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0021, dated 

January 20, 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–2014–0626. 

(2) For service information identified in 

this AD, contact Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, NJ 07606; 

telephone 201–440–6700; Internet http://

www.dassaultfalcon.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 

September 9, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–21915 Filed 9–12–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0701; Directorate 

Identifier 2014–CE–025–AD] 

RIN 2120–AA64 

Airworthiness Directives; Various de 

Havilland Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Harry E. Williams de Havilland Model 

DH 82A airplanes, all Cliff Robertson de 

Havilland Model DH 82A airplanes, and 

all de Havilland Model DH 83 airplanes. 

This proposed AD was prompted by 

reports of structural failure of the 

attachment of the wing to the fuselage 

that resulted from failed lateral fuselage 

tie rods. This proposed AD would 

require inspecting the aircraft 

maintenance records to determine the 


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54920 Federal Register / Vol. 79, No. 178 / Monday, September 15, 2014 / Proposed Rules 

date of installation or the date of last 

replacement of the lateral fuselage tie 

rods. This proposed AD would also 

require repetitively replacing all lateral 

fuselage tie rods and attaching nuts at a 

specified life limit interval. We are 

proposing this AD to correct the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed AD by October 30, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, for de Havilland DH 

82A airplanes, contact de Havilland 

Support Ltd., Building 213, Duxford 

Airfield, Cambridge, United Kingdom 

CB22 4QR, telephone: +44 (0) 1223 

830090; fax: +44 (0) 1223 83008; email: 

info@dhsupport.com, Internet: http://

www.dhsupport.com/moth.php. 

For service information identified in 

this proposed AD, for de Havilland DH 

83 airplanes, contact Air Stratus Ltd., 

Oaksey Park Airfield, Oaksey, 

Malmesbury, Wiltshite, United 

Kingdom SN 16 9SD, telephone: +44 (0) 

1666 575111; no known Internet 

address. 

You may view this referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64016. 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– 

0701; 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 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: For 

airplanes covered under Type 

Certificate Data Sheet (TCDS) A5PC 

(Model de Havilland DH 82A airplanes 

built in Australia): Andrew McAnaul, 

Aerospace Engineer, FAA, Fort Worth 

Airplane Certification Office, ASW–150 

(c/o San Antonio MIDO), 10100 

Reunion Place, Suite 650, San Antonio, 

Texas 78216; phone: (210) 308–3365; 

fax: (210) 308–3370; email: 

andrew.mcanaul@faa.gov. 

For airplanes covered under TCDS 

A8EU (Model de Havilland DH 82A 

airplanes built in the United Kingdom): 

Fred Guerin, Aerospace Engineer, FAA, 

Los Angeles Aircraft Certification 

Office, 3960 Paramount Blvd., Suite 

100, Lakewood, California 90712; phone 

(562) 627–5232; fax: (562) 627–5210; 

email: fred.guerin@faa.gov. 

For airplanes covered under TCDS 2– 

439 (Model de Havilland DH 83 

airplanes built in the United Kingdom): 

Karl Schletzbaum, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; phone: (816) 329–4123; 

fax: (816) 329–4090; email: 

karl.schletzbaum@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2014–0701; Directorate Identifier 2014– 

CE–025–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://

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 

During routine maintenance on a de 

Havilland Model DH 82 airplane, it was 

found that the lateral fuselage tie rod at 

the aft position had sheared at its 

location with the spar attachment 

fitting. Investigation revealed that the 

failure was a result of fatigue cracking 

in the thread root. In addition, the 

forward tie rod (which had not 

fractured) was distorted and found to 

have been manufactured from material 

of incorrect specification with a lower 

tensile strength. 

During our review of the abovereferenced cracking and the related 

mandatory service information, we 

determined that the life limit on the 

lateral fuselage tie rods is not currently 

addressed for airplanes on the U.S. 

registry. Mandatory service information 

is required for airplanes on the registry 

in certain other countries, but in the 

United States an AD must be issued to 

require the actions of a service bulletin 

for all airplanes. 

De Havilland Model DH 82A 

airplanes (commonly referred to as Tiger 

Moths) are type certificated under two 

type certificates. TCDS A5PC, currently 

held by Harry E. Williams, is for 

airplanes built in Australia, and TCDS 

A8EU, currently held by Cliff Robertson, 

c/o Gadbois Business Management, is 

for airplanes built in the United 

Kingdom. This type certification 

approval was not by validation, but by 

an acceptance process; as such, the U.S. 

type certificate holders are not the 

manufacturers of the airplanes and the 

original manufacturers (de Havilland 

and its licensees) are not type certificate 

holders. 

De Havilland Support Ltd (DHSL) 

holds the type certificate responsibility 

for de Havilland Model DH 82A 

airplanes (the type design for TCDS 

A8EU) in the United Kingdom. 

DHSL is custodian of the airframe 

design data, manufacturing drawings, 

and repair schemes still in existence for 

de Havilland Model DH 82A Tiger Moth 

series airplanes only. In 2012, DHSL 

entered into a CAA Type Responsibility 

Agreement (TRA) so that the airplane 

remains eligible, if required, for an 

ICAO-compliant Certificate of 

Airworthiness to facilitate training and 

pleasure flying. 

Similarly, Air Stratus Ltd holds the 

type certificate responsibility for de 

Havilland Model DH 83 airplanes (the 

type design for TCDS 2–439) in the 

United Kingdom. 

This condition, if not corrected, could 

result in structural failure of the 

attachment of the wing to the fuselage. 

We are issuing this proposed AD to 

correct the unsafe condition on these 

products. 

Relevant Service Information 

We reviewed British Aerospace 

Military Aircraft and Aerostructures 

BAe Aircraft Bulletin for de Havilland 

Moth Aircraft, Document Type and Ref 

No Technical News Sheet CT (Moth) No 

29, Issue 3, dated March 1, 1999, which 

was approved by the Civil Aviation 

Authority (CAA) for the United 

Kingdom to ensure the continued 


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airworthiness of these airplanes in the 

United Kingdom. The service 

information introduces a life limit for 

the lateral fuselage tie rods and 

describes procedures for repetitively 

replacing the lateral fuselage tie rods 

and attaching nuts. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 69 airplanes of U.S. 

registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspect the aircraft maintenance records to 

determine the date of installation or date 

of last replacement of the lateral fuselage tie rods and attaching nuts.

1 work-hour × $85 per hour = $85 Not applicable $85 $5,865 

We estimate the following costs to the 

necessary replacements. 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Replace lateral fuselage tie rods and attaching nuts ... 30 work-hours × $85 per hour = $2,550 ...................... $825 $3,375 

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): 

Harry E. Williams, Cliff Robertson, and de 

Havilland Airplanes: Docket No. FAA– 

2014–0701; Directorate Identifier 2019– 

CE–019–AD. 

(a) Comments Due Date 

We must receive comments by October 30, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Harry E. Williams and 

Cliff Robertson Model de Havilland DH 82A 

airplanes, all serial numbers, and de 

Havilland Model DH 83 airplanes, all serial 

numbers, certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 5341, Fuselage, Wing Attach Fittings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

structural failure of the attachment of the 

wing to the fuselage that resulted from failed 

lateral fuselage tie rods. We are issuing this 

AD to correct the unsafe condition on these 

products. 

(f) Compliance 

Comply with this AD within the 

compliance times specified in paragraphs (g) 

through (h) of this AD, unless already done. 


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54922 Federal Register / Vol. 79, No. 178 / Monday, September 15, 2014 / Proposed Rules 

(g) Determine Date of Installation or Date of 

Last Replacement of the Lateral Fuselage Tie 

Rods and Attaching Nuts 

Within the next 30 days after the effective 

date of this AD, review the aircraft records 

to determine the date of installation or date 

of last replacement of the lateral fuselage tie 

rods and attaching nuts. 

(h) Replace the Lateral Fuselage Tie Rod and 

Attaching Nuts 

Initially replace the lateral fuselage tie rod 

and attaching nuts at whichever of the 

compliance times specified in paragraph 

(h)(1) or paragraph (h)(2) of this AD that 

applies. Repetitively thereafter replace the 

lateral fuselage tie rod and attaching nuts 

every 2,000 hours TIS or 18 years, whichever 

occurs first. Do the replacement following the 

procedures in paragraph 2.C. of the 

Accomplishment Instructions and the table 

on Figure 1 in British Aerospace Military 

Aircraft and Aerostructures BAe Aircraft 

Bulletin for De Havilland Moth Aircraft, 

Document Type and Ref No Technical News 

Sheet CT (Moth) No 29, Issue 3, dated March 

1, 1999. 

(1) If the date of lateral fuselage tie rod 

installation or date of last replacement is 

known: Do the initial replacement at 

whichever of the following compliance times 

in paragraph (h)(1)(i) or paragraph (h)(1)(ii) of 

this AD that occurs later: 

(i) Upon accumulating 2,000 hours TIS on 

the lateral fuselage tie rod or upon reaching 

18 years from the last lateral fuselage tie rod 

replacement, whichever occurs first; or 

(ii) Within the next 6 months after the 

effective date of this AD or within the next 

100 hours TIS after the effective date of this 

AD, whichever occurs first. 

(2) If the date of lateral fuselage tie rod 

installation or date of last replacement is not 

known: Do the initial replacement within the 

next 6 months after the effective date of this 

AD or within the next 100 hours TIS after the 

effective date of this AD, whichever occurs 

first. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager of the Fort Worth 

Airplane Certification Office (ACO), the 

Manager of the Los Angeles Aircraft 

Certification Office (ACO), and the Manager 

of the Standards Office, FAA, have the 

authority to approve AMOCs for their 

respective products covered by 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 applicable FAA office, 

send it to the attention of the person 

identified in paragraphs (j)(1), (j)(2), or (j)(3), 

as applicable. 

(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. 

(j) Related Information 

(1) For more information about this AD for 

airplanes covered under Type Certificate 

Data Sheet (TCDS) A5PC (Model de 

Havilland DH 82A airplanes built in 

Australia), contact Andrew McAnaul, 

Aerospace Engineer, FAA, Fort Worth ACO, 

ASW–150 (c/o San Antonio MIDO), 10100 

Reunion Place, Suite 650, San Antonio, 

Texas 78216; phone: (210) 308–3365; fax: 

(210) 308–3370; email: andrew.mcanaul@

faa.gov. 

(2) For more information about this AD for 

airplanes covered under TCDS A8EU (Model 

de Havilland DH 82A airplanes built in the 

United Kingdom), contact Fred Guerin, 

Aerospace Engineer, FAA, Los Angeles ACO, 

3960 Paramount Blvd., Suite 100, Lakewood, 

California 90712; phone (562) 627–5232; fax: 

(562) 627–5210; email: fred.guerin@faa.gov. 

(3) For more information about this AD for 

airplanes covered under TCDS 2–439 (Model 

de Havilland DH 83 airplanes built in the 

United Kingdom), contact Karl Schletzbaum, 

Aerospace Engineer, FAA, Small Airplane 

Directorate, 901 Locust, Room 301, Kansas 

City, Missouri 64106; telephone: (816) 329– 

4123; fax: (816) 329–4090; email: 

karl.schletzbaum@faa.gov. 

(4) For British Aerospace Military Aircraft 

and Aerostructures BAe Aircraft Bulletin for 

De Havilland Moth Aircraft, Technical New 

Sheet CT (Moth) No 29, Issue 3, dated March 

1, 1999, service information identified in this 

AD, contact: 

(i) For de Havilland DH 82A airplanes: de 

Havilland Support Ltd, Building 213, 

Duxford Airfield, Cambridge, United 

Kingdom CB22 4QR, telephone: +44 (0) 1223 

830090; fax: +44 (0) 1223 83008; email: info@

dhsupport.com; Internet: http://

www.dhsupport.com/moth.php. 

(ii) For de Havilland DH 83 airplanes: Air 

Stratus Ltd., Oaksey Park Airfield, Oaksey, 

Malmesbury, Wiltshite, United Kingdom SN 

16 9SD, telephone: +44 (0) 1666 575111; no 

known Internet address. 

(5) You may view this service information 

at FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64016. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

Issued in Kansas City, Missouri, on 

September 8, 2014. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2014–21916 Filed 9–12–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0643; Directorate 

Identifier 2013–SW–059–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada (Bell) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2001–13– 

51 for Bell Model 206L–4, 407, and 427 

helicopters. AD 2001–13–51 currently 

requires inspecting certain driveshafts 

for a crack, a loose bolt or nut, or red 

powder residue and replacing a 

driveshaft if there is a crack, a loose bolt 

or nut, or red powder residue. AD 2001– 

13–51 also requires notifying the FAA 

within 10 days if a crack is found in the 

driveshaft. Since we issued AD 2001– 

13–51, the Model 429 helicopter has 

been certificated, and the reporting 

requirement is no longer necessary. This 

proposed AD would retain the 

inspection requirement of AD 2001–13– 

51, expand the applicability to include 

the Model 429 helicopter, and remove 

the reporting requirement. These 

proposed actions are intended to 

prevent failure of a driveshaft, loss of 

drive to the main rotor system, and a 

subsequent emergency landing. 

DATES: We must receive comments on 

this proposed AD by November 14, 

2014. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

foreign authority’s AD, the economic 

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 service information identified in 

this proposed AD, contact Bell 

Helicopter Textron Canada Limited, 

12,800 Rue de l’Avenir, Mirabel, Quebec 

J7J1R4; telephone (450) 437–2862 or 


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