25390 Federal Register / Vol. 74, No. 101 / Thursday, May 28, 2009 / Rules and Regulations 

reliability of the control itself, but rather 

determine the effects, including 

environmental effects addressed in 

§ 23.1309(e), on the airplane systems 

and engine control system when 

installing the control on the airplane. 

When appropriate, engine certification 

data may be used when showing 

compliance with this requirement; 

however, the effects of the installation 

on this data must be addressed. 

For these evaluations, the loss of 

FADEC control will be analyzed 

utilizing the threat levels associated 

with a catastrophic failure. 

Issued in Kansas City, Missouri on May 20, 

2009. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E9–12417 Filed 5–27–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0119; Directorate 

Identifier 2008–CE–068–AD; Amendment 

39–15916; AD 2009–11–06] 

RIN 2120–AA64 

Airworthiness Directives; M7 

Aerospace LP Models SA226–AT, 

SA226–T, SA226–TC, SA227–AC (C– 

26A), SA227–AT, SA227–BC (C–26A), 

SA227–CC, and SA227–DC (C–26B) 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) to 

supersede AD 2008–12–16, which 

applies to certain M7 Aerospace LP 

SA226 and SA227 series airplanes. AD 

2008–12–16 currently requires you to 

inspect wires and tube assemblies for 

chafing, arcing, or insufficient clearance 

between components. If chafing, arcing, 

or insufficient clearance between 

components is found, AD 2008–12–16 

requires you to clear, repair, and/or 

replace all chafed wires, components, 

and tube assemblies. AD 2008–12–16 

also requires you to cover the four-gauge 

wires leaving the battery box with 

firesleeving and secure them with a 

clamp. Since we issued AD 2008–12–16, 

M7 Aerospace LP has notified us that 

Model SA227–BC (C–26A) was 

inadvertently left out of the 

Applicability section of the AD, and 

they updated some of the service 

information due to parts availability. 

Operators have also identified issues 

with model applicability that needed 

clarification. Consequently, this AD 

retains the actions of AD 2008–12–16, 

adds Model SA227–BC (C–26A) to the 

Applicability section, and regroups the 

models for clarification. We are issuing 

this AD to detect and correct chafing of 

electrical wires, components, and tube 

assemblies. This condition could result 

in arcing of exposed wires with 

consequent burning of a hole in a 

hydraulic line or the bleed air line. This 

failure could lead to a hydraulic fluid 

leak and a possible fire in the engine 

nacelle compartment. 

DATES: This AD becomes effective on 

July 2, 2009. 

On July 2, 2009, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in Table 2 of this AD. 

As of July 23, 2008 (73 FR 34615, June 

18, 2008), the Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in Table 3 of this AD. 

ADDRESSES: For service information 

identified in this AD, contact M7 

Aerospace Repair Station, 10823 NE 

Entrance Road, San Antonio, Texas 

78216; telephone: (210) 824–9421; fax: 

(210) 804–7766; Internet: http:// 

www.m7aerospace.com. 

To view the AD docket, go to U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590, or on the Internet at http:// 

www.regulations.gov. The docket 

number is FAA–2009–0119; Directorate 

Identifier 2008–CE–068–AD. 

FOR FURTHER INFORMATION CONTACT: 

Werner Koch, Aerospace Engineer, 

ASW–150, Fort Worth Airplane 

Certification Office, 2601 Meacham 

Blvd., Fort Worth, Texas 76137; 

telephone: (817) 222–5133; fax: (817) 

222–5960. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On February 6, 2009, we issued a 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an AD that would apply to 

certain M7 Aerospace LP SA226 and 

SA227 series airplanes. This proposal 

was published in the Federal Register 

as a notice of proposed rulemaking 

(NPRM) on February 12, 2009 (74 FR 

7006). The NPRM proposed to 

supersede AD 2008–12–16 with a new 

AD that would retain the actions of AD 

2008–12–16, add the Model SA227–BC 

(C–26A) to the Applicability section, 

and regroup the models for clarification. 

Comments 

We provided the public the 

opportunity to participate in developing 

this AD. The following presents the 

comment received on the proposal and 

FAA’s response: 

Comment Issue: Inspection 

Applicability 

George L. Smith commented that it 

was unclear if paragraph (e)(3) of the AD 

applied to airplanes with batteries 

mounted in the nose of the airplane or 

if the AD only applied to airplanes with 

the battery located in the wing leading 

edge. 

As specified in the Applicability 

section, this AD applies to all serial 

numbers regardless of where the battery 

is located. Therefore the actions 

required in paragraph (e)(3) of this AD 

apply to all airplanes listed in the 

Applicability section regardless of 

where the battery is located. For added 

clarity we are adding the applicable 

serial numbers to the paragraph. 

We are changing the final rule AD by 

adding the applicable serial numbers to 

each action based on this comment. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed except for 

the change previously discussed and 

minor editorial corrections. We have 

determined that these minor 

corrections: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Costs of Compliance 

We estimate that this AD affects 268 

airplanes in the U.S. registry. 

We estimate the following costs to do 

the inspection: 

Federal Register / Vol. 74, No. 101 / Thursday, May 28, 2009 / Rules and Regulations 25391 

Labor cost Parts cost Total cost per 

airplane 

Total cost on 

U.S. operators 

4 work-hours × $80 per hour = $320 ........................................ Not Applicable .................................................. $320 $85,760 

We estimate the following costs to do 

any necessary modifications for certain 

Models SA226–AT, SA226–T, SA226– 

TC, SA227–AC, and SA227–AT 

airplanes referenced in M7 Aerospace 

SA226 Series Service Bulletin 226–24– 

019, revised: November 21, 2008; or M7 

Aerospace SA227 Series Service 

Bulletin 227–24–001, revised: 

November 21, 2008. We estimate 88 

airplanes may need this modification: 

Labor cost Parts cost Total cost per 

airplane 

Total cost on 

U.S. operators 

13 work-hours × $80 per hour = $1,040 ..................................................................................... $7 $1,047 $92,136 

We estimate the following costs to do 

any necessary repairs for certain Models 

SA226–AT, SA226–TC, SA227–AC, and 

SA227–AT referenced in M7 Aerospace 

SA226 Series Service Bulletin 226–24– 

020, revised: August 4, 2008; or M7 

Aerospace SA227 Series Service 

Bulletin 227–24–002, revised: 

November 21, 2008. We have no way of 

determining the number of airplanes 

that may need this repair: 

Labor cost Parts cost Total cost per 

airplane 

50 work-hours × $80 per hour = $4,000 ................................................................................................................. $3,000 $7,000 

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 AD. 

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 this AD: 

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 a summary of the costs 

to comply with this AD (and other 

information as included in the 

Regulatory Evaluation) and placed it in 

the AD Docket. You may get a copy of 

this summary by sending a request to us 

at the address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2009–0119; 

Directorate Identifier 2008–CE–068– 

AD’’ in your request. 

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 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. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2008–12–16, Amendment 39–15560 (73 

FR 34615, June 18, 2008), and adding 

the following new AD: 

2009–11–06 M7 Aerospace LP: Amendment 

39–15916; Docket No. FAA–2009–0119; 

Directorate Identifier 2008–CE–068–AD. 

Effective Date 

(a) This AD becomes effective on July 2, 

2009. 

Affected ADs 

(b) This AD supersedes AD 2008–12–16, 

Amendment 39–15560. 

Applicability 

(c) This AD applies to Models SA226–AT, 

SA226–T, SA226–TC, SA227–AC (C–26A), 

SA227–AT, SA227–BC (C–26A), SA227–CC, 

and SA227–DC (C–26B) airplanes, all serial 

numbers, that are certificated in any category. 

Unsafe Condition 

(d) This AD results from five reports of 

chafing between the bleed air tube assembly 

and the electrical starter cables on M7 

Aerospace LP SA226 and SA227 series 

airplanes with one incident resulting in a 

fire. We are issuing this AD to detect and 

correct chafing of electrical wires and 

components, hydraulic tube assemblies, and 

bleed air tube assemblies. This condition 

could result in arcing of the exposed wires 

with consequent burning of a hole in a 

hydraulic line or the bleed air line. This 

failure could lead to a possible hydraulic 

fluid leak and fire in the engine nacelle 

compartment. 

Compliance 

(e) To address this problem, you must do 

the following, unless already done: 

25392 Federal Register / Vol. 74, No. 101 / Thursday, May 28, 2009 / Rules and Regulations 

TABLE 1—ACTIONS, COMPLIANCE, AND PROCEDURES

Actions Compliance Procedures 

(1) For the following model and serial number 

(S/N) airplanes, inspect the main battery 

leads running forward from the battery compartment for deterioration, cover the fourgauge wires leaving the battery box with 

firesleeving, and secure them with a clamp: 

(i) SA226–AT, S/N AT–001 through AT– 

419; 

(ii) SA226–T, S/N T–201 through T–248; 

(iii) SA226–TC, S/N TC–201 through TC– 

419; 

(iv) SA227–AC (C–26A), S/N AC–420 

through AC–539, AC–541, AC–543, AC– 

544, AC–547 through AC–551; and 

(v) SA227–AT, S/N AT–423 through AT– 

551. 

Within 250 hours time-in-service (TIS) after 

July 23, 2008 (the effective date of AD 

2008–12–16). 

Use the following service information as applicable: 

(A) For Models SA226–AT, SA226–T, 

and SA226–TC airplanes: Follow M7 

Aerospace SA226 Series Service Bulletin No. 226–24–019, revised: November 21, 2008; or Fairchild Aircraft Corporation SA226 Series Service Bulletin 

No. SB 24–019, revised: May 17, 1983; 

or 

(B) For Models SA227–AC (C–26A) and 

SA227–AT airplanes: Follow M7 Aerospace SA227 Series Service Bulletin 

No. 227–24–001, revised: November 

21, 2008; or Fairchild Aircraft Corporation SA227 Series Service Bulletin No. 

SB24–001, revised: May 17, 1983. 

(2) For the following model and S/N airplanes, 

reroute the hydraulic tube assemblies in the 

right wing leading edge, reroute the battery 

cables and 22-gauge wire bundle, and install 

a new access panel forward of the battery 

box: 

(i) SA226–AT, S/N AT–001 through AT– 

074; 

(ii) SA226–TC, S/N TC–201 through TC– 

419; 

(iii) SA227–AC (C–26A), S/N AC–420 

through AC–539, AC–541, AC–543, AC– 

544, AC–547 through AC–550; and 

(iv) SA227–AT, S/N AT–423 through AT– 

551. 

Before further flight after the modification required in paragraph (e)(1) of this AD and 

you were not able to obtain a minimum 

0.50-inch clearance between the bleed air 

line and the tubing on the battery cables. 

Use the following service information as applicable: 

(A) For Models SA226–AT, and SA226– 

TC airplanes: Follow M7 Aerospace 

SA226 Series Service Bulletin No. 

226–24–020, revised: August 4, 2008; 

or Fairchild Aircraft Corporation SA226 

Series Service Bulletin No. SB 24–020, 

revised: February 15, 1984; or 

(B) For Models SA227–AC (C–26A) and 

SA227–AT, airplanes: Follow M7 Aerospace SA227 Series Service Bulletin 

No. 227–24–002, revised: November 

21, 2008; or Fairchild Aircraft Corporation SA227 Series Service Bulletin No. 

SB24–002, revised: February 15, 1984. 

(3) For model SA226–AT, SA226–T, SA226– 

TC, SA227–AC (C–26A), SA227–AT, 

SA227–CC, and SA227–DC (C–26B) airplanes, all S/N: Inspect electrical wires and 

components, hydraulic tube assemblies, and 

bleed air tube assemblies at the left hand 

and right hand (LH/RH) inboard wing leading 

edge/battery box areas, LH/RH wing stations 

51.167 to 81.174, and at all feed-through locations into the LH/RH inboard keelson for 

any evidence of chafing or arcing. 

Within 250 hours TIS after July 23, 2008 (the 

effective date of AD 2008–12–16). Repetitively thereafter inspect at intervals not to 

exceed 12 months. 

Use the following service information as applicable: 

(i) For Models SA226–AT, SA226–T, and 

SA226–TC airplanes: Follow M7 Aerospace SA226 Series Service Bulletin No. 

226–24–036, revised November 21, 

2008; or M7 Aerospace SA226 Series 

Service Bulletin No. 226–24–036, issued: 

September 19, 2007; 

(ii) For Models SA227–AC (C–26A) and 

SA227–AT, airplanes: Follow M7 Aerospace SA227 Series Service Bulletin No. 

227–24–019, revised: November 21, 

2008; or M7 Aerospace SA227 Series 

Service Bulletin No. 227–24–019, issued: 

September 19, 2007; or 

(iii) For Models SA227–CC and SA227–DC 

(C–26B) airplanes: Follow SA227 Series 

Commuter Category Service Bulletin No. 

CC7–24–010, revised November 21, 

2008; or SA227 Series Commuter Category Service Bulletin No. CC7–24–010, 

issued September 19, 2007. 

(4) For model SA227–BC (C–26A) airplanes, 

all S/N: Inspect the main battery leads running forward from the battery compartment 

for any evidence of insulation deterioration. 

Within 250 hours TIS after July 2, 2009 (the 

effective date of this AD). 

Follow M7 Aerospace SA227 Series Service 

Bulletin No. 227–24–001, revised: November 21, 2008. 

(5) For model SA227–BC (C–26A) airplanes, 

all S/N: Inspect electrical wires and components, hydraulic tube assemblies, and bleed 

air tube assemblies at LH/RH inboard wing 

leading edge/battery box areas, LH/RH wing 

stations 51.167 to 81.174, and at all feedthrough locations into the LH/RH inboard 

keelson for any evidence of insulation deterioration, chafing, or arcing. 

Within 250 hours TIS after July 2, 2009 (the 

effective date of this AD). Repetitively thereafter inspect at intervals not to exceed 12 

months. 

Follow M7 Aerospace SA227 Series Service 

Bulletin No. 227–24–019, revised: November 21, 2008. 

Federal Register / Vol. 74, No. 101 / Thursday, May 28, 2009 / Rules and Regulations 25393 

TABLE 1—ACTIONS, COMPLIANCE, AND PROCEDURES—Continued 

Actions Compliance Procedures 

(6) For all model and S/N airplanes: Clear, repair, and/or replace all electrical wires and 

components, hydraulic tube assemblies, and 

bleed air tube assemblies, in the inspection 

area and feed-through locations that show 

any sign of insulation deterioration, chafing, 

or arcing, as required. 

Before further flight after any inspection required in paragraphs (e)(1), (e)(3), (e)(4), 

and (e)(5) of this AD where any evidence of 

insulation deterioration, chafing, or arcing 

was found. 

Use the service information from paragraphs 

(e)(1), (e)(3), (e)(4), and (e)(5) of this AD, 

as applicable. 

Note: Although not a requirement of this 

AD, you may incorporate Swearingen 

Aviation Corporation SA226 Series Service 

Bulletin No. 57–010, revised: December 5, 

1975, on those airplanes that have not 

installed the access panel. Installation of the 

access panel will simplify the incorporation 

of the service bulletins referenced in this AD 

and future inspections of the areas of 

concern. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Fort Worth Airplane 

Certification 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: Werner Koch, 

Aerospace Engineer, ASW–150, Fort Worth 

Airplane Certification Office, 2601 Meacham 

Blvd., Fort Worth, Texas 76137; telephone: 

(817) 222–5133; fax: (817) 222–5960. 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 

Material Incorporated by Reference 

(g) You must use the service information 

specified in Table 2 or Table 3 of this AD to 

do the actions required by this AD, unless the 

AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information listed in Table 2 of 

this AD under 5 U.S.C. 552(a) and 1 CFR part 

51. 

TABLE 2—MATERIAL INCORPORATED BY REFERENCE

Service Bulletin No. Date 

(i) M7 Aerospace SA226 Series Service Bulletin No. 226–24–019 ...................................................................... Revised: November 21, 2008. 

(ii) M7 Aerospace SA226 Series Service Bulletin No. 226–24–020 ..................................................................... Revised: August 4, 2008. 

(iii) M7 Aerospace SA226 Series Service Bulletin No. 226–24–036 .................................................................... Revised: November 21, 2008. 

(iv) M7 Aerospace SA227 Series Service Bulletin No. 227–24–001 .................................................................... Revised: November 21, 2008. 

(v) M7 Aerospace SA227 Series Service Bulletin No. 227–24–002 ..................................................................... Revised: November 21, 2008. 

(vi) M7 Aerospace SA227 Series Service Bulletin No. 227–24–019 .................................................................... Revised: November 21, 2008. 

(vii) M7 Aerospace SA227 Series Commuter Category Service Bulletin No. CC7–24–010 ................................ Revised: November 21, 2008. 

(2) On July 23, 2008 (73 FR 34615, June 18, 

2008), the Director of the Federal Register 

approved the incorporation by reference of 

the service information listed in Table 3 of 

this AD. 

TABLE 3—PREVIOUS MATERIAL INCORPORATED BY REFERENCE

Service Bulletin No. Date 

(i) Fairchild Aircraft Corporation SA226 Series Service Bulletin No. SB 24–019 ................................................. Revised: May 17, 1983. 

(ii) Fairchild Aircraft Corporation SA226 Series Service Bulletin No. SB 24–020 ................................................ Revised: February 15, 1984. 

(iii) M7 Aerospace SA226 Series Service Bulletin No. 226–24–036 .................................................................... Issued: September 19, 2007. 

(iv) Fairchild Aircraft Corporation SA227 Series Service Bulletin No. SB24–001 ................................................ Revised: May 17, 1983. 

(v) Fairchild Aircraft Corporation SA227 Series Service Bulletin No. SB24–002 ................................................. Revised: February 15, 1984. 

(vi) M7 Aerospace SA227 Series Service Bulletin No. 227–24–019 .................................................................... Issued: September 19, 2007. 

(vii) M7 Aerospace SA227 Series Commuter Category Service Bulletin No. CC7–24–010 ................................ Issued: September 19, 2007. 

25394 Federal Register / Vol. 74, No. 101 / Thursday, May 28, 2009 / Rules and Regulations 

(3) For service information identified in 

this AD, contact M7 Aerospace Repair 

Station, 10823 NE Entrance Road, San 

Antonio, Texas 78216; telephone: (210) 824– 

9421; fax: (210) 804–7766; Internet: http:// 

www.m7aerospace.com. 

(4) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(5) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri, on May 

18, 2009. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E9–11989 Filed 5–27–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0482; Directorate 

Identifier 2008–SW–54–AD; Amendment 39– 

15920; AD 2009–11–10] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH Model EC135 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter Deutschland GmbH 

(Eurocopter) Model EC135 helicopters. 

This AD results from a report of 

abnormal main rotor blade vibrations on 

a Eurocopter Model EC135 helicopter. 

This AD also results from mandatory 

continuing airworthiness information 

(MCAI) issued by the European Aviation 

Safety Agency (EASA), which is the 

Technical Agent for the Member States 

of the European Community. The MCAI 

states that an operator reported unusual 

vibrations during the start phase of the 

main rotor blade on one helicopter. The 

vibrations stopped after the application 

of torque. Subsequent maintenance 

personnel found that six of the eight 

attachment screws of the lower hubshaft bearing support were loose. This 

condition was discovered in two 

additional helicopters. Loose screws in 

the bearing support, if not detected and 

corrected, could result in abnormal 

main rotor blade vibrations and 

subsequent damage to the main 

transmission. 

DATES: This AD becomes effective on 

June 12, 2009. 

The incorporation by reference of 

certain publications is approved by the 

Director of the Federal Register as of 

June 12, 2009. 

We must receive comments on this 

AD by July 27, 2009. 

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 your 

comments electronically. 

• 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 (972) 641–3460, fax (972) 

641–3527, or at http:// 

www.eurocopter.com. 

Examining the 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, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is 

stated in the ADDRESSES section of this 

AD. Comments will be available in the 

AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Chinh Vuong, Aviation Safety Engineer, 

FAA, Rotorcraft Directorate, Safety 

Management Group, Fort Worth, Texas 

76193–0111, telephone (817) 222–5116, 

fax (817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We recently received a report of 

abnormal main rotor blade vibration on 

a Eurocopter Model EC135 helicopter. 

This main rotor blade vibration 

occurred after initial aircraft start, while 

operating at flat pitch, between 8.5 and 

25 percent torque and 98.6 percent NR/ 

N2 speed, and dissipated once the 

FADEC switches were advanced to 

FLIGHT. The main rotor transmission 

chip light also illuminated with 

minimal debris found on the chip 

detectors. During troubleshooting, six of 

the eight main transmission lower hubshaft bearing support bolts were found 

lying in the bottom of the main 

transmission case, atop of the lower 

transmission access panel. Only two of 

the eight bolts remained installed, loose 

in their positions, and the outer race of 

the roller bearing was rotated out of 

position (cocked). Approximately three 

weeks after that first incident, we 

received a report that loose bolts were 

discovered on two additional newer 

helicopters that had not been inspected 

at the time the loose bolts were 

discovered on the first helicopter. 

Subsequent investigations revealed that 

screws were not properly torqued and 

vibrations had caused the screws to 

back-out. Loosened screws in the 

bearing support, if not detected and 

corrected, could result in abnormal 

main rotor blade vibrations and 

subsequent damage to the main 

transmission. 

EASA has issued EASA Emergency 

AD 2008–0175–E, dated September 16, 

2008, to correct an unsafe condition for 

the Eurocopter Model EC135 

helicopters. The MCAI explains that 

‘‘The lower hub-shaft bearing consists of 

a ball bearing and a roller bearing. The 

outer race of the roller bearing is fixed 

to the housing with screws. Should all 

attachment screws become loose, the 

outer race of the roller bearing might 

separate, which would constitute an 

unsafe condition. In such case, however, 

the axial guidance of the rotor hub-shaft 

would still be ensured.’’ The MCAI 

requires inspecting the main 

transmission attachment hardware and 

installing locking washers. You may 

obtain further information by examining 

the MCAI and any related service 

information in the AD docket. 

Related Service Information 

Eurocopter has issued Alert Service 

Bulletin EC135–63A–013, Revision 2, 

dated September 12, 2008 (ASB). The 

ASB specifies checking the screws at the 

lower hub-shaft bearing for correct 

attachment and securing attachment 

hardware by means of locking washers. 

The actions described in the MCAI are 

intended to correct the same unsafe 

condition as that identified in the 

service information.