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contains regulatory documents having general

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are keyed to and codified in the Code of

Federal Regulations, which is published under

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Rules and Regulations Federal Register

36629 

Vol. 79, No. 125 

Monday, June 30, 2014 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0385; Directorate 

Identifier 2013–SW–079–AD; Amendment 

39–17879; AD 2014–13–04] 

RIN 2120–AA64 

Airworthiness Directives; Columbia 

Helicopters, Inc. (Type Certificate 

Previously Held by Boeing Defense & 

Space Group) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Columbia Helicopters, Inc. (Columbia) 

Model 234 helicopters. This AD requires 

visually and tap inspecting each fore 

and aft rotor blade for any defect, 

damage, or a disbond and, if necessary, 

repairing or replacing the blade. Also, 

this AD requires dye-penetrant 

inspecting the aft pylon structure for 

fatigue cracking in certain areas near the 

attachment fittings and, if there is a 

crack, repairing or replacing the aft 

pylon. This AD is prompted by an 

accident caused by fatigue failure of an 

aft pylon fitting attach structure 

combined with aft rotor blade damage. 

The actions specified by this AD are 

intended to detect fatigue cracks in the 

aft pylon attach structure to prevent 

overload of the aft pylon structure and 

failure of the rotor blade, rotor blade 

vibration, departure of the aft pylon, 

and subsequent loss of control of the 

helicopter. 

DATES: This AD becomes effective July 

15, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of July 15, 2014. 

We must receive comments on this 

AD by August 29, 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 AD, any 

incorporated by reference service 

information, 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 AD, contact Columbia Helicopters, 

Inc., 14452 Arndt Road NE., Aurora OR 

97002, telephone (503) 678–1222, fax 

(503) 678–5841, or at http://

www.colheli.com/. 

You may review the referenced 

service information at the FAA, Office 

of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 

663, Fort Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: 

Kathleen Arrigotti, Aviation Safety 

Engineer, Seattle Aircraft Certification 

Office, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue SW., Renton, 

Washington 98057; telephone (425) 

917–6426; email kathleen.arrigotti@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. We will file 

in the docket all comments that we 

receive, as well as a report summarizing 

each substantive public contact with 

FAA personnel concerning this 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

We are adopting a new AD for 

Columbia Model 234 helicopters. This 

AD requires visually and tap inspecting 

each rotor blade for any defect, damage, 

or disbond. If there is a defect, damage, 

or a disbond, this AD requires the blade 

to be repaired or replaced before further 

flight. Also, this AD requires dyepenetrant inspecting the aft pylon 

structure for a crack in the area of the 

station (STA) 534 and 594 tension 

attachment fittings. If there is a crack, 

this AD requires repairing or replacing 

the aft pylon before further flight. This 

AD is prompted by an accident caused 

by fatigue failure of the structure 

surrounding the aft pylon following an 

aft rotor blade failure. Due to existing 

blade damage, a portion of an aft rotor 

blade separated from the aircraft, 

causing vibration, which accelerated 

fatigue cracking of the aft pylon 

surrounding structure and overloaded 

the structure to failure. This caused the 

aft pylon to separate from the aircraft. 

The actions specified in this AD are 

intended to detect cracks in the aft 

pylon surrounding structure and 

defects, damage, or disbonds in the rotor 

blades and to prevent separation of a 

portion of the rotor blade, vibration, 

overload of the aft pylon surrounding 

structure, departure of the aft pylon, and 


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36630 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Rules and Regulations 

subsequent loss of control of the 

helicopter. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other helicopters of this 

same type design. 

Related Service Information 

Columbia issued Service Bulletin No. 

234–54–0004, Revision 0, dated 

November 22, 2013 (SB 234–54–0004), 

specifying an initial and recurring dyepenetrant inspection to detect and 

correct cracking of the aft pylon 

structure at the STA 534 and 594 

tension attachment fittings. If a crack is 

found, SB 234–54–0004 specifies 

contacting the manufacturer before 

further flight. 

Columbia also issued Service Bulletin 

No. 234–62–0008, Revision 1, dated 

December 6, 2013 (SB 234–62–0008), 

specifying recurring visual inspections 

of the entire rotor blade for defects, 

damage and disbonds and recurring tap 

inspections of the rotor blade trailing 

edge for disbonding conditions. If any 

damage or disbond is detected, SB 234– 

62–0008 specifies referring to the 

maintenance manual for serviceability 

and repair, contacting the manufacturer 

for repair assistance, or replacing the 

blade before further flight. 

AD Requirements 

This AD requires: 

• Within 50 hours time-in-service (TIS): 

Æ Cleaning, visually inspecting, and 

tap inspecting each rotor blade for 

a defect, damage, or disbond. 

Æ Repairing any defect, damage, or 

disbond if within acceptable limits, 

and replacing the blade if beyond 

acceptable limits, before further 

flight. 

• Within 50 hours TIS and thereafter at 

intervals not to exceed 100 hours 

TIS, inspecting the aft pylon at STA 

534 and 594 as follows: 

Æ Dye-penetrant inspecting the aft 

pylon at the attachment fittings and 

surrounding structure for a crack. 

Æ If there is a crack, before further 

flight, repairing or replacing the aft 

pylon. 

This AD prohibits installing an aft 

pylon or a rotor blade until these 

inspections are accomplished. 

Differences Between This AD and the 

Service Information 

This AD does not require the 500- 

hour TIS inspection of the rotor blade or 

the 3,000 hour TIS after initial 

inspection of the pylon structure as 

specified in the service information. We 

plan to publish a notice of proposed 

rulemaking to give the public an 

opportunity to comment on those longterm requirements. Also, this AD does 

not require contacting the manufacturer. 

Interim Action 

We consider this AD to be an interim 

action. The design approval holder is 

currently developing a terminating 

action that will address the unsafe 

condition identified in this AD. Once 

this terminating action is identified, we 

might consider further rulemaking then. 

Costs of Compliance 

We estimate that this AD affects 4 

helicopters of U.S. Registry. We estimate 

that operators may incur the following 

costs to comply with this AD. Labor 

costs are estimated at $85 per hour. We 

estimate 1 work hour to visually inspect 

all blades, 6 work hours to dyepenetrant inspect the pylon, and 4 work 

hours to do the tap test inspection. 

Based on these estimates, the total cost 

is $935 per helicopter and $3,740 for the 

U.S. fleet. To replace a blade, we 

estimate 4 work hours and $250,000 for 

parts, for a total cost of $250,340 per 

helicopter. 

FAA’s Justification and Determination 

of the Effective Date 

Providing an opportunity for public 

comments before adopting these AD 

requirements would delay 

implementing the safety actions needed 

to correct this known unsafe condition. 

Therefore, we find that the risk to the 

flying public justifies waiving notice 

and comment prior to adopting this rule 

because of the severity of the failure and 

high rate of occurrence for repairs in 

blades and cracks in the pylon on other 

aircraft. Also, the required corrective 

actions must be done within 50 hours 

TIS, a very short time period based on 

the average flight-hour utilization rate of 

these helicopters. The repetitive 

inspections are required at intervals not 

to exceed 100 hours TIS, which can be 

reached within as short a time as 2 

weeks. 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we determined that notice an 

opportunity for public comment before 

issuing this AD are impracticable and 

contrary to the public interest and that 

good cause exists for making this 

amendment effective in less than 30 

days. 

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, and 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 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, I certify 

that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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. 


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Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Rules and Regulations 36631 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2014–13–04 Columbia Helicopters, Inc. 

(Type Certificate Previously Held By 

Boeing Defense & Space Group) 

Helicopters: Amendment 39–17879; 

Docket No. FAA–2014–0385; Directorate 

Identifier 2013–SW–079–AD. 

(a) Applicability 

This AD applies to Model 234 helicopters, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

fatigue failure of aft pylon fitting attach 

structure combined with aft rotor blade 

damage. This condition could result in 

failure of a fore or aft rotor blade, vibration, 

overload of the aft pylon structure at the 

pylon attach fittings, departure of the aft 

pylon, and subsequent loss of control of the 

helicopter. 

(c) Effective Date 

This AD becomes effective July 15, 2014. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) Within 50 hours time-in-service (TIS): 

(i) Clean and inspect each fore and aft rotor 

blade for a defect, damage, or a disbond in 

accordance with the Accomplishment 

Instructions, paragraph 3.A.(1)(b) through 

3.A.(2)(b), of Columbia Helicopters, Inc., 

Service Bulletin No. 234–62–0008, Revision 

1, dated December 6, 2013 (SB 234–62–0008). 

(ii) Using a metallic coin or tap hammer, 

tap inspect each rotor blade trailing edge for 

defect, damage, or a disbond in accordance 

with the Accomplishment Instructions, 

paragraph 3.B.(1) through 3.B.(2)(e) and 

Figures 1 and 2 of SB 234–62–0008. 

(iii) If there is any defect, damage, or a 

disbond, repair the blade before further 

flight. If the defect, damage, or disbond is 

beyond acceptable limits, replace the blade 

before further flight. 

(2) Within 50 hours TIS and thereafter at 

intervals not to exceed 100 hours TIS, inspect 

the aft pylon at the station 534 and 594 

tension attachment fittings as follows: 

(i) Dye-penetrant inspect the aft pylon at 

the attachment fitting for a crack as shown 

in Figures 1, 2, and 3 and by following the 

Detailed Special Inspection-Dye Penetrant 

Method, paragraph 2.A.(2) through 2.G.(1), of 

Columbia Helicopters, Inc. Service Bulletin 

No. 234–54–0004, Revision 0, dated 

November 22, 2013 (SB 234–54–0004). 

(ii) If there is a crack, before further flight, 

repair or replace the aft pylon. Figures 2, 3, 

4, and 5 of SB 234–54–0004 contain 

examples of a crack. 

(3) Do not install an aft pylon or a rotor 

blade until the requirements of paragraphs 

(e)(1) and (e)(2) of this AD are accomplished. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

9-ANM-Seattle-ACO-AMOC-Requests@

faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5400 and 6210 Nacelle/Pylon Structure 

and Main Rotor Blades. 

(h) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) Columbia Helicopters, Inc., Service 

Bulletin No. 234–54–0004, Revision 0, dated 

November 22, 2013. 

(ii) Columbia Helicopters, Inc., Service 

Bulletin No. 234–62–0008, Revision 1, dated 

December 6, 2013. 

(3) For service information identified in 

this AD, contact Columbia Helicopters, Inc., 

14452 Arndt Road NE., Aurora, OR 97002, 

telephone (503) 678–1222, fax (503) 678– 

5841, or at http://www.colheli.com/. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on June 16, 

2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–14800 Filed 6–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0862; Directorate 

Identifier 2012–NM–098–AD; Amendment 

39–17863; AD 2014–12–02] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Dassault Aviation Model FALCON 2000 

and FALCON 2000EX airplanes. This 

AD was prompted by a determination 

that new center of gravity (CG) limits are 

applicable during takeoff with certain 

conditions. This AD requires revising 

the airplane flight manual (AFM) to 

include procedures to advise the 

flightcrew of the new CG limits. We are 

issuing this AD to prevent an erratic 

takeoff path and consequent reduced 

controllability of the airplane. 

DATES: This AD becomes effective 

August 4, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 4, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/#!docketDetail;D=

FAA-2013-0862; or in person at the 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC. 

For Dassault 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.dassault

falcon.com. For Aviation Partners, Inc. 

service information identified in this 

AD, contact Aviation Partners, Inc., 

7299 Perimeter Road South, Seattle, WA 

98108; telephone 800–946–4638; 

Internet http://www.aviation

partners.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. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 


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