Federal Register / Vol. 75, No. 150 / Thursday, August 5, 2010 / Rules and Regulations 47201 

Revision G, dated December 8, 2009, under 

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

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of TIMCO Service Bulletin TSB– 

88–52–045, Revision E, dated November 6, 

2008, on July 6, 2010 (75 FR 38017, July 1, 

2010). 

(3) For service information identified in 

this AD, contact TIMCO Aviation Services, 

815 Radar Road, Greensboro, North Carolina 

27410–6221; telephone 336–668–4410, 

extension 3063; fax 336–662–8330; Internet: 

http://www.timco.aero. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(5) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

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

to http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on July 16, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–18620 Filed 8–4–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0713; Directorate 

Identifier 2009–SW–63–AD; Amendment 39– 

16369; AD 2010–15–03] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model EC 130 B4 Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

specified Eurocopter France helicopters. 

This action requires inspecting certain 

electrical harnesses for damage and if 

damage is found, repairing the electrical 

harness; protecting the electrical 

harness from damage; installing harness 

clamp blocks; and inspecting each 

fairing attachment screw to determine 

the length and replacing attachment 

screws, if they exceed a certain length. 

This amendment is prompted by a 

report of an in-flight incident that led to 

the inflation of the emergency floatation 

gear (emergency floats) and the 

activation of various warnings. The 

actions specified in this AD are 

intended to prevent interference 

between an electrical harness and the 

lower structure fairing attachment 

screws. Damage to an electrical harness 

by a lower structure fairing attachment 

screw could lead to short-circuiting of 

various warnings, inflation of the 

emergency floats during flight, and 

subsequent loss of control of the 

helicopter. 

DATES: Effective August 20, 2010. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of August 20, 

2010. 

Comments for inclusion in the Rules 

Docket must be received on or before 

October 4, 2010. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD: 

• 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. 

You may get the service information 

identified in this AD from American 

Eurocopter Corporation, 2701 Forum 

Drive, Grand Prairie, TX 75053–4005, 

telephone (800) 232–0323, fax (972) 

641–3710, or at http:// 

www.eurocopter.com. 

Examining the Docket: You may 

examine the docket that contains the 

AD, any comments, and other 

information 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 Docket 

Operations office (telephone (800) 647– 

5527) is located in Room W12–140 on 

the ground floor of the West Building at 

the street address stated in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

DOT/FAA Southwest Region, George 

Schwab, Aviation Safety Engineer, 

ASW–112, Rotorcraft Directorate, Safety 

Management Group, 2601 Meacham 

Blvd., Fort Worth, Texas 76137, 

telephone (817) 222–5114, fax (817) 

222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

This amendment adopts a new AD for 

Eurocopter France Model EC 130 B4 

helicopters that have been modified in 

accordance with MOD 073774, and have 

not had MOD 073591 nor the 

modification specified in Eurocopter 

Drawing No. 350A085340 incorporated. 

This action requires, within 10 hours 

time-in-service (TIS), removing the 

lower forward right-hand, left-hand, and 

center lower structure fairings (fairings); 

inspecting each electrical harness for 

chaffing, tears, holes, or other damage at 

the location of each attachment screw 

and repairing any damage; protecting 

electrical harnesses by wrapping them 

with electrical tape; installing harness 

clamp blocks; and inspecting each 

attachment screw to determine the 

length and replacing any attachment 

screw that is longer than 14mm. This 

amendment is prompted by a report of 

an in-flight incident in which an 

attachment screw that secures the righthand lower center fairing damaged the 

electrical harness and caused several 

short circuits, resulting in the described 

incident. This condition, if not detected, 

could lead to inflation of the emergency 

floats during flight, and subsequent loss 

of control of the helicopter. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD No. 2006– 

0344 R1, dated May 10, 2007, to correct 

an unsafe condition for Eurocopter 

France Model EC 130 B4 helicopters. 

EASA advises that their AD was 

initially issued as an Emergency AD, 

following a report of an in-flight 

incident which led to activation of 

various warning lights and inflation of 

the emergency floats. The pilot was able 

to land the helicopter without damage. 

EASA AD No. 2006–0344 R1 revises 

EASA Emergency AD 2006–0344–E, 

dated November 13, 2006. 

Related Service Information 

Eurocopter France has issued 

Emergency Alert Service Bulletin 

(EASB) No. 88A001 R1, dated April 17, 

2007, which specifies procedures for 

detecting and correcting interference 

between an electrical harness and a 

fairing attachment screw. The EASA 

classified this EASB as mandatory and 

issued AD No. 2006–0344 R1, dated 

May 10, 2007, to ensure the continued 

airworthiness of these helicopters. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
47202 Federal Register / Vol. 75, No. 150 / Thursday, August 5, 2010 / Rules and Regulations 

FAA’s Evaluation and Unsafe Condition 

Determination 

This helicopter has been approved by 

the aviation authority of France and is 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, their 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by the EASA and determined 

the unsafe condition exists and is likely 

to exist or develop on other helicopters 

of this same type design. 

Differences Between This AD and the 

EASA AD 

This AD requires inspections by a 

qualified mechanic rather than checks, 

which may be conducted by a pilot. 

Also, this AD requires contacting the 

FAA, Safety Management Group, ASW– 

112, instead of contacting Eurocopter 

France to define a certain customized 

repair solution before returning the 

helicopter to flight configuration if 4 or 

more electrical wires or cables need 

repair. Additionally, this AD uses the 

term ‘‘hours time-in-service’’ instead of 

‘‘flight hours’’. 

FAA’s Determination and Requirements 

of This AD 

This unsafe condition is likely to exist 

or develop on other helicopters of the 

same type design. Therefore, this AD is 

being issued to prevent, on helicopters 

post MOD 073774, any interference 

between an electrical harness and an 

attachment screw. Embodiment of a 

modification in accordance with 

Eurocopter drawing 350A085342 is 

considered to be a temporary solution to 

be applied rapidly in order to ensure 

that there is no interference. 

Embodiment of a modification in 

accordance with Eurocopter Drawing 

350A085340 is the permanent solution. 

The EASA AD has been revised to 

provide additional information that 

MOD 073591 also is a permanent 

solution and has been incorporated on 

new helicopters. This AD requires 

removing the fairings; inspecting each 

electrical harness for any chaffing, tear, 

hole, or other damage at the location of 

each attachment screw and repairing 

any damage; protecting electrical 

harnesses by wrapping them with 

electrical tape; installing harness clamp 

blocks; and inspecting each attachment 

screw to determine the length and 

replacing any that are longer than 

14mm. 

Accomplish the actions by following 

specified portions of the EASB 

described previously. The short 

compliance time involved is required 

because the previously described 

critical unsafe condition can adversely 

affect the controllability of the 

helicopter. Therefore, inspecting each 

electrical harness for damage at the 

location of each attachment screw and 

repairing any damage, if found; 

protecting the electrical harness by 

wrapping with electrical tape; installing 

harness clamp blocks; and inspecting 

each attachment screw to determine the 

length and replacing any that are longer 

than 14mm, are required within 10 

hours time-in-service (TIS), a short 

compliance time, and this AD must be 

issued immediately. 

Since a situation exists that requires 

the immediate adoption of this 

regulation, it is found that notice and 

opportunity for prior public comment 

hereon are impracticable, and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Costs of Compliance 

We estimate that this AD will affect 

about 13 helicopters of U.S. registry. We 

also estimate that it will take about 12 

work-hours per helicopter to remove the 

lower structure fairings; inspect an 

electrical harness for interference and 

damage; repair an electrical harness, if 

necessary; shorten the attachment 

screws; install harness clamp blocks; 

and reinstall the lower fairings. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $120 per 

helicopter. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators is $1,140 per helicopter, 

$14,820 for the entire fleet. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

written data, views, or arguments 

regarding this AD. Send your comments 

to an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2010–0713; 

Directorate Identifier 2009–SW–63–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the AD. We will consider all comments 

received by the closing date and may 

amend the AD in light 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 with FAA 

personnel concerning this AD. Using the 

search function of the docket Web site, 

you can find and read the comments to 

any of our dockets, including the name 

of the individual who sent the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national Government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the 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); and 

3. 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. See the AD docket to examine 

the economic evaluation. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in subtitle VII, 

part A, subpart III, section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
Federal Register / Vol. 75, No. 150 / Thursday, August 5, 2010 / Rules and Regulations 47203 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by adding 

a new airworthiness directive to read as 

follows: 

2010–15–03 Eurocopter France: 

Amendment 39–16369. Docket No. 

FAA–2010–0713; Directorate Identifier 

2009–SW–63–AD. 

Applicability: Model EC 130 B4 helicopters 

that have been modified in accordance with 

MOD 073774, and have not had MOD 073591 

nor the modification specified in Eurocopter 

Drawing No. 350A085340 incorporated, 

certificated in any category. 

Compliance: Required within 10 hours 

time-in-service (TIS), unless accomplished 

previously. 

To detect interference and prevent damage 

to an electrical harness by a lower structure 

fairing attachment screw (attachment screw), 

which could lead to short-circuiting of 

various warnings, inflation of the emergency 

floatation gear (emergency floats) during 

flight, and subsequent loss of control of the 

helicopter, accomplish the following: 

(a) Remove the lower forward right-hand, 

left-hand, and center fairings. 

(b) Inspect each electrical harness for 

chaffing, a tear, a hole, or other damage at the 

location of each attachment screw as 

depicted in Details B, C, and D in Figure 1 

in Eurocopter Emergency Alert Service 

Bulletin No. 88A001 R1, dated April 17, 2007 

(EASB), and as shown at point (a) in Figure 

2 and Figure 3 in the EASB. 

(1) If there is no chaffing, tear, hole, or 

other damage to the electrical harness at any 

attachment screw: 

(i) Determine the length of each attachment 

screw that secures the fairings. Replace any 

attachment screw that is longer than 14mm 

with an airworthy attachment screw, part 

number (P/N) A0164TK050S014X; 

(ii) Install the spacer on the electrical 

harness in accordance with paragraph 

2.B.3.a. of the Accomplishment Instructions 

of the EASB; 

(iii) Relocate the electrical harness on the 

cable holders in accordance with paragraph 

2.B.3.b. of the Accomplishment Instructions 

of the EASB; and 

(iv) Install the harness clamp blocks in 

accordance with paragraph 2.B.4. of the 

Accomplishment Instructions of the EASB. 

(2) If there is chaffing, a tear, a hole, or 

other damage to an electrical harness at the 

location of an attachment screw, remove any 

protective tape from the electrical harness as 

shown at point (b) in Figure 2 of the EASB 

and inspect the insulation on each electrical 

wire and cable strand for chaffing, a tear, a 

hole, or other damage at the attachment 

screw location. 

(i) If there is no chaffing, tear, hole, or 

other damage to the insulation on any wire 

or cable strand, wrap the electrical harness 

with protective tape and comply with 

paragraphs (b)(1)(i) through (b)(1)(iv) of this 

AD. 

(ii) If there is chaffing, a tear, a hole, or 

other damage to the insulation on any 

electrical wire or cable strand, but the 

electrical wire or cable strand is not 

damaged, wrap the electrical wire or cable 

strand that has damaged insulation with 

protective tape and wrap the electrical 

harness with protective tape, then comply 

with paragraphs (b)(1)(i) through (b)(1)(iv) of 

this AD. 

(c) If 3 or less electrical wires or cable 

strands in the same immediate area are 

damaged: 

(1) Repair each damaged electrical wire or 

cable strand with an extension lead, P/N 

E0541–10, in accordance with the Appendix 

to the EASB; test the electrical continuity of 

the repaired electrical wire or cable strand 

using an ohmmeter, continuity test light, or 

equivalent device; and functionally test the 

system affected by the repair; 

(2) Wrap the electrical harness with 

protective tape; and 

(3) Comply with paragraphs (b)(1)(i) 

through (b)(1)(iv) of this AD. 

(d) If 4 or more electrical wires or cable 

strands in the same immediate area are 

damaged: 

(1) Contact the Safety Management Group, 

Rotorcraft Directorate, FAA, ATTN: George 

Schwab, Aviation Safety Engineer, 2601 

Meacham Blvd., Fort Worth, Texas, 76137, 

telephone (817) 222–5114, fax (817) 222– 

5961, for an approved electrical conductor 

repair procedure; and 

(2) Comply with (b)(1)(i) through (b)(1)(iv) 

of this AD. 

(e) Reinstall the fairings. 

(f) Contact the Manager, Safety 

Management Group, Rotorcraft Directorate, 

FAA, ATTN: George Schwab, Aviation Safety 

Engineer, 2601 Meacham Blvd., Fort Worth, 

Texas, 76137, telephone (817) 222–5114, fax 

(817) 222–5961, for information about 

previously approved alternative methods of 

compliance. 

(g) The Joint Aircraft System/Component 

(JASC) Code is 3297: Landing Gear System 

Wiring. 

(h) The inspections, modifications and 

repairs, if needed, shall be done in 

accordance with the specified portions of 

Eurocopter Emergency Alert Service Bulletin 

No. 88A001 R1, dated April 17, 2007. The 

Director of the Federal Register approved this 

incorporation by reference in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Copies may be obtained from American 

Eurocopter Corporation, 2701 Forum Drive, 

Grand Prairie, TX 75053–4005, telephone 

(800) 232–0323, fax (972) 641–3710, or at 

http://www.eurocopter.com. Copies may be 

inspected at the FAA, Office of the Regional 

Counsel, Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas or 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/code_of_federal_

regulations/ibr_locations.html. 

(i) This amendment becomes effective on 

August 20, 2010. 

Note: The subject of this AD is addressed 

in European Aviation Safety Agency (France) 

AD No. 2006–0344 R1, dated May 10, 2007, 

which revises European Aviation Safety 

Agency Emergency AD No. 2006–0344–E, 

dated November 13, 2006. 

Issued in Fort Worth, Texas, on July 8, 

2010. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–17282 Filed 8–4–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0403; Directorate 

Identifier 2007–NM–166–AD; Amendment 

39–16379; AD 2010–16–03] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Corporation Model MD–11 and 

MD–11F Airplanes Equipped With 

General Electric CF6–80C2 Series 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Model MD–11 and MD–11F airplanes. 

This AD requires revising the airplane 

flight manual to advise the flightcrew to 

use certain procedures during descent 

in certain icing conditions. This AD 

results from reports of several in-flight 

engine flameouts, including multiple 

dual engine flameout events, in icecrystal icing conditions. We are issuing 

this AD to ensure that the flightcrew has 

the proper procedures to follow in 

certain icing conditions. These certain 

icing conditions could cause a multiple 

engine flameout during flight with the 

potential inability to restart the engines, 

and consequent forced landing of the 

airplane. 

DATES: This AD is effective September 9, 

2010. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

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

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1