Federal Register / Vol. 74, No. 101 / Thursday, May 28, 2009 / Rules and Regulations 25399 

LIST OF EFFECTIVE PAGES

Page title/description Page number(s) Revision number Date shown on 

page(s) 

AMM Title Page ........................................................................................................... 1 19 January 15, 2008. 

Chapter 05 List of Effective Pages: 

1–2 * January 15, 2008. 

Subsection 05–10–00: 

1–2 * January 15, 2008. 

* Not shown. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact BAE Systems Regional 

Aircraft, 13850 McLearen Road, Herndon, 

Virginia 20171; telephone 703–736–1080; email raebusiness@baesystems.com; Internet 

http://www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 

(3) 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 or 425–227–1152. 

(4) 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 May 15, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–11997 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–2009–0486; Directorate 

Identifier 2009–NM–064–AD; Amendment 

39–15919; AD 2009–11–09] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 Airplanes and Airbus Model 

A300–600 Airplanes 

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 the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

An A300–600 operator reported a recent 

event which occurred during the take-off roll, 

where a SOGERMA co-pilot seat slid back 

uncommanded to the end position. The seat 

horizontal movement actuator was replaced 

on the affected co-pilot seat. At the following 

take-off roll the same event occurred, the copilot seat sliding back uncommanded again. 

* * * 

An unwanted movement of pilot or copilot seat in the horizontal direction is 

considered as potentially unsafe, especially 

during the take-off phase when the speed of 

the aeroplane is greater than 100 knots and 

until landing gear retraction. 

* * * * * 

Uncommanded movement of the pilot 

and co-pilot seats during takeoff or 

landing could interfere with the 

operation of the airplane and, as a 

result, could cause consequent loss of 

control of the airplane. This AD requires 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: This AD becomes effective June 

12, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of June 12, 2009. 

We must receive comments on this 

AD by June 29, 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 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 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, 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, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety 

Agency, which is the aviation authority 

for the Technical Agent for the Member 

States of the European Community, has 

issued Airworthiness Directive 2009– 

0084, dated April 9, 2009 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

An A300–600 operator reported a recent 

event which occurred during the take-off roll, 

where a SOGERMA co-pilot seat slid back 

uncommanded to the end position. The seat 

horizontal movement actuator was replaced 

on the affected co-pilot seat. At the following 

take-off roll the same event occurred, the copilot seat sliding back uncommanded again. 

Further to these events, the inspection 

carried out on the two removed actuators 

ARTUS Part Number (P/N) RT19H4FX, 

revealed that the clutch was broken inside 

the shaft, thus unlocking the seat horizontal 

movement. 

An unwanted movement of pilot or copilot seat in the horizontal direction is 

considered as potentially unsafe, especially 

during the take-off phase when the speed of 

the aeroplane is greater than 100 knots and 

until landing gear retraction. 

For the reasons described above and 

pending the development of a permanent 

solution, this AD requires the deactivation of 

the electrical powered SOGERMA pilot seats 

25400 Federal Register / Vol. 74, No. 101 / Thursday, May 28, 2009 / Rules and Regulations 

2510112 series and co-pilot seats 2510113 

series. 

In addition, this AD provides two 

(optional) interim solutions in order to 

restore a partial seat electrical adjustment 

(vertical only) or a full seat electrical 

adjustment (vertical and horizontal) by 

accomplishment of intermediate actions. 

Uncommanded movement of the pilot 

and co-pilot seats during takeoff or 

landing could interfere with the 

operation of the airplane and, as a 

result, could cause consequent loss of 

control of the airplane. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued All Operators Telex 

(AOT) A310–25A2203, Revision 02, 

dated March 2, 2009; and AOT A300– 

25A6215, Revision 02, dated March 2, 

2009. EADS SOGERMA has issued Alert 

Service Bulletin A2510112–25–764, 

Revision 1, dated February 17, 2009; 

and Inspection Service Bulletin 

2510112–25–807, dated February 20, 

2009. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between the AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a Note within the AD. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because an uncommanded 

movement of the pilot and co-pilot seats 

during takeoff or landing could cause 

consequent loss of control of the 

airplane. Therefore, we determined that 

notice and opportunity for public 

comment before issuing this AD are 

impracticable and that good cause exists 

for making this amendment effective in 

fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2009–0486; 

Directorate Identifier 2009–NM–064– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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 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 regulatory 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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2009–11–09 Airbus: Amendment 39–15919. 

Docket No. FAA–2009–0486; Directorate 

Identifier 2009–NM–064–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 12, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A310– 

203, A310–204, A310–221, A310–222, A310– 

304, A310–322, A310–324, and A310–325 

airplanes; and Airbus Model A300 B4–601, 

A300 B4–603, A300 B4–605R, A300 B4–620, 

A300 B4–622, A300 B4–622R, A300 C4–605R 

Variant F, A300 F4–605R and A300 F4–622R 

airplanes; certificated in any category; all 

serial numbers having SOGERMA 2510112 

series pilot electrical seats or SOGERMA 

2510113 series co-pilot electrical seats 

installed. 

Federal Register / Vol. 74, No. 101 / Thursday, May 28, 2009 / Rules and Regulations 25401 

Subject 

(d) Air Transport Association (ATA) of 

America Code 25: Equipment/Furnishings. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

An A300–600 operator reported a recent 

event which occurred during the take-off roll, 

where a SOGERMA co-pilot seat slid back 

uncommanded to the end position. The seat 

horizontal movement actuator was replaced 

on the affected co-pilot seat. At the following 

take-off roll the same event occurred, the copilot seat sliding back uncommanded again. 

Further to these events, the inspection 

carried out on the two removed actuators 

ARTUS Part Number (P/N) RT19H4FX, 

revealed that the clutch was broken inside 

the shaft, thus unlocking the seat horizontal 

movement. 

An unwanted movement of pilot or copilot seat in the horizontal direction is 

considered as potentially unsafe, especially 

during the take-off phase when the speed of 

the aeroplane is greater than 100 knots and 

until landing gear retraction. 

For the reasons described above and 

pending the development of a permanent 

solution, this AD requires the deactivation of 

the electrical powered SOGERMA pilot seats 

2510112 series and co-pilot seats 2510113 

series. 

In addition, this AD provides two 

(optional) interim solutions in order to 

restore a partial seat electrical adjustment 

(vertical only) or a full seat electrical 

adjustment (vertical and horizontal) by 

accomplishment of intermediate actions. 

Uncommanded movement of the pilot and 

co-pilot seats during takeoff or landing could 

interfere with the operation of the airplane 

and, as a result, could cause consequent loss 

of control of the airplane. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 15 days after the effective date 

of this AD: Deactivate the electrical supply of 

SOGERMA 2510112 series pilot seats and 

SOGERMA 2510113 series co-pilot seats, in 

accordance with the instructions of Airbus 

All Operators Telex (AOT) A310–25A2203, 

Revision 02, dated March 2, 2009; or AOT 

A300–25A6215, Revision 02, dated March 2, 

2009; as applicable. 

(2) For optional intermediate action for 

restoration of the electrical adjustment of the 

vertical seat movement only: Deactivating the 

electrical powered horizontal movement of 

SOGERMA 2510112 series pilot seats or 

SOGERMA 2510113 series co-pilot seats, in 

accordance with the instructions of EADS 

SOGERMA Alert Service Bulletin A2510112– 

25–764, Revision 1, dated February 17, 2009, 

allows restoration of the vertical adjustment 

only. 

(3) For optional intermediate action for 

restoration of the electrical adjustment of the 

vertical seat and horizontal seat movement: 

Inspecting the position of switch ‘S4’ and the 

related shim of SOGERMA 2510112 series 

pilot seats or SOGERMA 2510113 series copilot seats, in accordance with EADS 

SOGERMA Inspection Service Bulletin 

2510112–25–807, dated February 20, 2009, 

allows reactivation of both horizontal and 

vertical electrical movements, provided the 

measurement results of the inspection are 

within the acceptable value indicated in the 

service bulletin, and provided that the 

inspection is repeated thereafter at intervals 

not to exceed 2 months. If the measurement 

result of any inspection is not within the 

acceptable value indicated in the EADS 

SOGERMA Inspection Service Bulletin 

2510112–25–807, dated February 20, 2009, 

the horizontal movement must be deactivated 

before further flight. 

(4) At the applicable time specified in 

paragraph (f)(4)(i) or (f)(4)(ii) of this AD: 

Submit a report of the findings for the first 

inspection done in accordance with 

paragraph (f)(3) of this AD to Airbus SAS— 

EAW (Airworthiness Office), 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France. The report must include a detailed 

fleet inspection report, including 

measurement values, and pin and serial 

numbers for each seat. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(ii) If the inspection was accomplished 

prior to the effective date of this AD: Submit 

the report within 30 days after the effective 

date of this AD. 

(5) Modifications made prior to the 

effective date of this AD in accordance with 

EADS SOGERMA Alert Service Bulletin 

A2510112–25–764, dated December 19, 2008, 

are considered acceptable for compliance 

with the applicable action specified in this 

AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: None. 

Other FAA AD Provisions 

(g) 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. 

Send information to ATTN: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference this AD. 

(2) Airworthy Product: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer or other source, 

use these actions if they are FAA-approved. 

Corrective actions are considered FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2009– 

0084, dated April 9, 2009; and the service 

information listed in Table 1 of this AD for 

related information. 

TABLE 1—RELATED SERVICE INFORMATION

Document Revision 

level Date 

Airbus All Operators Telex A300–25A6215 ............................................................................................................ 02 March 2, 2009. 

Airbus All Operators Telex A310–25A2203 ............................................................................................................ 02 March 2, 2009. 

EADS SOGERMA Alert Service Bulletin A2510112–25–764 ................................................................................. 1 February 17, 2009. 

EADS SOGERMA Inspection Service Bulletin 2510112–25–807 .......................................................................... (1) February 20, 2009. 

1Original. 

Material Incorporated by Reference 

(i) You must use Airbus All Operators 

Telex A310–25A2203, Revision 02, dated 

March 2, 2009; or Airbus All Operators Telex 

A300–25A6215, Revision 02, dated March 2, 

2009; as applicable; to do the actions 

required by this AD, unless the AD specifies 

otherwise. If you do the optional actions 

specified by this AD, you must use EADS 

SOGERMA Inspection Service Bulletin 

2510112–25–807, dated February 20, 2009; or 

EADS SOGERMA Alert Service Bulletin 

A2510112–25–764, Revision 1, dated 

February 17, 2009; as applicable; to perform 

those actions, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

25402 Federal Register / Vol. 74, No. 101 / Thursday, May 28, 2009 / Rules and Regulations 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; e-mail: account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(3) 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 or 425–227–1152. 

(4) 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 May 15, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–12322 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–2009–0453; Directorate 

Identifier 2008–SW–63–AD; Amendment 39– 

15911; AD 2009–11–01] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH (ECD) Model MBB– 

BK 117 A–1, A–3, A–4, B–1, B–2, and 

C–1 Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the specified ECD model helicopters 

that currently requires initial and 

repetitive inspections of the main rotor 

blade (blade) upper and lower surfaces 

for bulging. This AD 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, based on reported 

incidents in which a balance weight 

migrated toward the tip of the blade. 

The MCAI states that new blades have 

become available that are not fitted with 

lead balance weights. The MCAI states 

that only blades equipped with a lead 

balance weight may result in the unsafe 

condition. This AD retains the 

requirements of the current AD but 

limits the applicability to those partnumbered blades that are fitted with 

lead balance weights. The actions are 

intended to limit the applicability to 

those blades fitted with lead balance 

weights that could detach, migrate, and 

cause severe vibrations leading to blade 

failure and subsequent loss of control of 

the helicopter. 

DATES: This AD becomes effective on 

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: 

Sharon Miles, Aviation Safety Engineer, 

FAA, Rotorcraft Directorate, Regulations 

and Guidance Group, Fort Worth, Texas 

76193–0111, telephone (817) 222–5122, 

fax (817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

EASA, which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2008– 

0156, dated August 19, 2008, to 

supersede Luftfahrt-Bundesamt (LBA) 

Germany AD D–1994–280R3 (EASA 

approval 2005–6229) issued on 

September 19, 2005. Since the LBA AD 

was issued, new blades have become 

available that do not have lead balance 

weights. The LBA AD was issued 

following reports of two flight incidents 

involving balance weights detaching 

from the blade structure and migrating 

toward the tip of the blade causing 

severe vibrations. The centrifugal force 

on the blades can bring about creep 

deformation of the lead balance weight 

resulting in bulging of the blade skin. 

The height of such bulges is the criteria 

for assessing the extent of possible 

damage to the structure around the lead 

balance weight and the possibility of 

blade failure. The EASA AD states, 

‘‘only MR blades equipped with a lead 

balance weight are affected by this 

unsafe condition.’’ The EASA AD also 

states that current requirements are 

retained but limits the applicability to 

those part-numbered blades that are 

fitted with lead balance weights. The 

actions are intended to limit the 

applicability to those blades with lead 

balance weights that could detach, 

migrate, and cause severe vibrations 

leading to blade failure and subsequent 

loss of control of the helicopter. 

You may obtain further information 

by examining the MCAI and any related 

service information in the AD docket. 

Related Service Information 

ECD has issued Alert Service Bulletin 

MBB–BK117–10–108, Revision 3, dated 

August 7, 2008 (ASB). This ASB limits 

the applicability to certain partnumbered blades with a lead balance 

weight. This ASB replaces Revision 2. 

Revision 3 of the ASB states that if one 

of the previous revisions has been done, 

no further work is required due to 

Revision 3. The ASB notes that ‘‘the 

inspection interval was incorporated in 

the MBB–BK117 Maintenance Manual 

(MM) with Revision No. 24 (for MBB– 

BK117 A–1 through B–2) and with 

Revision No. 5 (for MBB–BK117 C–1).’’ 

The ASB also notes that ‘‘provided that 

the first inspection has been 

accomplished during 5 flight hours and 

upon availability of these changes in the 

MM, the ASB–MBB–BK117–10–108 will 

no longer be effective.’’ The ASB further 

states that if one of the editions of this 

ASB before Revision 3 has been done, 

you should inspect the blades for 

bulging by following the MM and at the