34222 Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2009–14–11 Turbomeca S.A.: Amendment 

39–15961. Docket No. FAA–2009–0330; 

Directorate Identifier 2008–NE–43–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 19, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Turbomeca S.A. 

ARRIUS 2F turboshaft engines with P3 air 

pipe, part number 0319719180, installed. 

These engines are installed on, but not 

limited to, Eurocopter EC120B helicopters. 

Reason 

(d) Rubs between the pipe and the 

bulkhead may lead to premature wearing and 

finally rupture of the P3 air pipe. The loss 

of P3 air pressure would then force the fuel 

control system to idle which could have a 

detrimental effect in critical phases of flight. 

We are issuing this AD to prevent an 

uncommanded power loss, which could 

result in an emergency autorotation landing 

or accident. 

Actions and Compliance 

(e) Unless already done, do the following 

actions within 100 operating hours after the 

effective date of this AD. Use paragraphs 

2.B.(1) through 2.C.(2) of Turbomeca 

Mandatory Service Bulletin No. 319 75 4810, 

dated May 14, 2008. 

(1) Visually inspect P3 air pipe (first 

section) and RH rear half-wall. 

(2) Inspect play between P3 air pipe (first 

section) and RH rear half-wall. 

(3) Replace P3 air pipe (first section) if any 

damage is found. 

(4) Readjust the first section of the P3 air 

pipe if the inspected clearance is found to be 

not compliant. 

(5) If the play after readjusting the first 

section of the P3 air pipe is still less than 0.5 

mm, repeat paragraphs (e)(1) through (e)(4) of 

this AD within intervals of 100 hours timesince-last inspection. 

(6) Replace RH rear half-wall if any damage 

is found. 

FAA AD Differences 

(f) None. 

Other FAA AD Provisions 

(g) Alternative Methods of Compliance 

(AMOCs): The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(h) Refer to MCAI EASA Airworthiness 

Directive 2008–0134R1, dated February 17, 

2009, and Turbomeca S.A. Mandatory 

Service Bulletin No. 319 75 4810, dated May 

14, 2008, for related information. Contact 

Turbomeca, 40220 Tarnos, France; telephone 

33 (0)5 59 74 40 00; telex 570 042; fax 33 (0)5 

59 74 45 15, for a copy of this service 

information. 

(i) Contact James Lawrence, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: james.lawrence@faa.gov; 

telephone (781) 238–7176; fax (781) 238– 

7199, for more information about this AD. 

Material Incorporated by Reference 

(j) You must use Turbomeca Mandatory 

Service Bulletin No. 319 75 4810, dated May 

14, 2008 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 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Turbomeca, 40220 Tarnos, 

France; telephone 33 (0)5 59 74 40 00; telex 

570 042; fax 33 (0)5 59 74 45 15. 

(3) You may review copies at the FAA, 

New England Region, 12 New England 

Executive Park, Burlington, MA; 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/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

June 30, 2009. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–16113 Filed 7–14–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0137; Directorate 

Identifier 2008–NM–201–AD; Amendment 

39–15967; AD 2009–15–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200 and –300, and A340–200 and 

–300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

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: 

Several reports have been received from 

A330 and A340 operators concerning chafing 

of the electrical harness behind the lavatory, 

located at L (level) 53, resulting in a number 

of short-circuits. This harness contains cables 

for lighting, plugs, loudspeakers and oxygen 

controls and indications. 

This condition, if not corrected, could lead 

to the short circuit of wires dedicated to 

oxygen, which, in case of emergency, could 

result in a large number of passenger oxygen 

masks (up to 32% of all seats) not being 

supplied with oxygen, possibly causing 

personal injuries. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

August 19, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 19, 2009. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on February 23, 2009 (74 FR 

8036). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Several reports have been received from 

A330 and A340 operators concerning chafing 

of the electrical harness behind the lavatory, 

located at L (level) 53, resulting in a number 

of short-circuits. This harness contains cables 

for lighting, plugs, loudspeakers and oxygen 

controls and indications. 

This condition, if not corrected, could lead 

to the short circuit of wires dedicated to 

oxygen, which, in case of emergency, could 

result in a large number of passenger oxygen 

masks (up to 32% of all seats) not being 

supplied with oxygen, possibly causing 

personal injuries. 

For the reasons described above, AD 2008– 

0154 was issued to require a wiring 

modification of the affected harnesses on 

right and left sides of the passenger 

compartment between frames (FR) 39.1 and 

39.2 and between FR 53.3 and 53.4, on premodification 48825 aircraft (i.e. nonenhanced cabin). 


srobinson on DSKHWCL6B1PROD with RULES
Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations 34223 

Since that AD was issued, it has been 

found that due to discrepancies in the 

referenced Airbus Service Bulletin (SB) at 

original issue, the modification should have 

been mandated at Revision 1 of the SB, rather 

than indicating that application of the SB at 

original issue is acceptable. 

For that reason, this EASA (European 

Aviation Safety Agency) AD retains the 

requirements of EASA AD 2008–0154, which 

is superseded, amends the requirement to 

specify that the SB must be accomplished at 

Revision 1 and that for aircraft on which the 

SB at original issue has already been 

accomplished, additional work must be done. 

* * * * * 

The modification includes rerouting the 

affected electrical harnesses and 

replacing certain wiring mounts and 

brackets in the passenger compartment. 

For all airplanes, additional work is 

required. The additional work includes 

interchanging certain fixed brackets and 

modifying certain wiring routing. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Actions Since the NPRM Was Issued 

We have received revisions to the 

service information specified in the 

NPRM. Airbus issued Mandatory 

Service Bulletin A330–92–3066, 

Revision 02, dated March 19, 2009; and 

Mandatory Service Bulletin A340–92– 

4071, Revision 03, dated March 19, 2009 

(‘‘the service bulletins’’). The actions 

described in the service bulletins are 

intended to correct the unsafe condition 

identified in the MCAI. Those revisions 

of the service bulletins include editorial 

changes, clarifying language, and no 

substantive changes to the 

Accomplishment Instructions. No 

additional work is required for airplanes 

modified by Airbus Mandatory Service 

Bulletin A330–92–3066, Revision 01, 

dated August 1, 2008; and Airbus 

Mandatory Service Bulletin A340–92– 

4071, Revision 02, dated November 28, 

2008. 

We have changed paragraphs (f)(1), 

(f)(2), and (h) to refer to the new 

revisions of the service bulletins, and 

added Airbus Mandatory Service 

Bulletin A330–92–3066, Revision 01; 

and Airbus Mandatory Service Bulletin 

A340–92–4071, Revision 02; to 

paragraph (f)(3) as acceptable for 

complying with the requirements of 

paragraphs (f)(1) and (f)(2) of this AD. 

EASA, which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2008–0161R1, 

dated March 23, 2009 (referred to after 

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

condition for the specified products. 

That MCAI differs from MCAI EASA AD 

2008–0161, dated August 25, 2008, 

which is referenced in the NPRM, by 

adding a paragraph extending the 

compliance time to 24 months from the 

20 months stated in the MCAI 

referenced in the NPRM. We have 

included that additional paragraph of 

the new MCAI in the quoted material in 

paragraph (e) of this AD, and changed 

paragraph (f) of this AD to reflect the 

new compliance time stated in the 

MCAI. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Differences Between This 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 our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 9 

products of U.S. registry. We also 

estimate that it will take 210 work-hours 

per product to comply with the basic 

requirements of this AD. The average 

labor rate is $80 per work-hour. 

Required parts will cost about $0 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of this AD 

to the U.S. operators to be $151,200, or 

$16,800 per product. 

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. 

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 the NPRM, 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. 


srobinson on DSKHWCL6B1PROD with RULES
34224 Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations 

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: 

2009–15–04 Airbus: Amendment 39–15967. 

Docket No. FAA–2009–0137; Directorate 

Identifier 2008–NM–201–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 19, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model A330–201, 

–202, –203, –223, –243, –301, –302, –303, 

–321, –322, –323, –341, –342, and –343 series 

airplanes; and Model A340–211, –212, –213, 

–311, –312, and –313 series airplanes; all 

manufacturer serial numbers, certificated in 

any category, except those on which Airbus 

Modification 48825 has been embodied in 

production. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 92. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Several reports have been received from 

A330 and A340 operators concerning chafing 

of the electrical harness behind the lavatory, 

located at L (level) 53, resulting in a number 

of short-circuits. This harness contains cables 

for lighting, plugs, loudspeakers and oxygen 

controls and indications. 

This condition, if not corrected, could lead 

to the short circuit of wires dedicated to 

oxygen, which, in case of emergency, could 

result in a large number of passenger oxygen 

masks (up to 32% of all seats) not being 

supplied with oxygen, possibly causing 

personal injuries. 

For the reasons described above, AD 2008– 

0154 was issued to require a wiring 

modification of the affected harnesses on 

right and left sides of the passenger 

compartment between frames (FR) 39.1 and 

39.2 and between FR 53.3 and 53.4, on premodification 48825 aircraft (i.e. nonenhanced cabin). 

Since that AD was issued, it has been 

found that due to discrepancies in the 

referenced Airbus Service Bulletin (SB) at 

original issue, the modification should have 

been mandated at Revision 1 of the SB, rather 

than indicating that application of the SB at 

original issue is acceptable. 

For that reason, this EASA (European 

Aviation Safety Agency) AD retains the 

requirements of EASA AD 2008–0154, which 

is superseded, amends the requirement to 

specify that the SB must be accomplished at 

Revision 1 and that for aircraft on which the 

SB at original issue has already been 

accomplished, additional work must be done. 

Th[e] Revision 1 [of EASA AD 2008–0161] 

is issued to extend the compliance time, 

which originally was 20 months, to 24 

months * * * after the effective date of this 

AD. * * * 

The modification includes rerouting the 

affected electrical harnesses and replacing 

certain wiring mounts and brackets in the 

passenger compartment. For all airplanes, 

additional work is required. The additional 

work includes interchanging certain fixed 

brackets and modifying certain wiring 

routing. 

Actions and Compliance 

(f) Unless already done, within 24 months 

after the effective date of this AD, do the 

following actions, as applicable. 

(1) Except as required by paragraph (f)(2) 

of this AD, modify the affected passenger 

compartment electrical harnesses, including 

the ‘‘ADDITIONAL WORK,’’ in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–92– 

3066, Revision 02, dated March 19, 2009; or 

Airbus Mandatory Service Bulletin A340–92– 

4071, Revision 03, dated March 19, 2009; as 

applicable. 

(2) For airplanes that have already been 

modified prior to the effective date of this AD 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

92–3066, dated November 27, 2007; or 

Airbus Service Bulletin A340–92–4071, 

dated November 27, 2007; as applicable: 

Accomplish the ‘‘ADDITIONAL WORK’’ in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–92–3066, Revision 02, dated 

March 19, 2009; or Airbus Mandatory Service 

Bulletin A340–92–4071, Revision 03, dated 

March 19, 2009; as applicable. 

(3) Actions accomplished according to the 

Airbus service information identified in 

Table 1 of this AD, including the 

‘‘ADDITIONAL WORK,’’ as applicable, are 

acceptable for complying with the 

requirements of paragraphs (f)(1) and (f)(2) of 

this AD. 

TABLE 1—ACCEPTABLE SERVICE INFORMATION

Airbus Mandatory Service Bulletin Revision Date 

A330–92–3066 ................................................................................................................................................ 01 August 1, 2008. 

A340–92–4071 ................................................................................................................................................ 01 August 1, 2008. 

A340–92–4071 ................................................................................................................................................ 02 November 28, 2008. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

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: Vladimir 

Ulyanov, Aerospace Engineer, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 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. 

(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 FAA-approved 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 EASA Airworthiness 

Directive 2008–0161R1, dated March 23, 

2009, and the service information listed in 

Table 2 of this AD, for related information. 


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Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations 34225 

TABLE 2—RELATED SERVICE INFORMATION

Airbus Mandatory Service Bulletin Revision Date 

A330–92–3066 ................................................................................................................................................ 01 August 1, 2008. 

A330–92–3066 ................................................................................................................................................ 02 March 19, 2009. 

A340–92–4071 ................................................................................................................................................ 01 August 1, 2008. 

A340–92–4071 ................................................................................................................................................ 02 November 28, 2008. 

A340–92–4071 ................................................................................................................................................ 03 March 19, 2009. 

Material Incorporated by Reference 

(i) You must use the applicable service 

information contained in 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 

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 SA—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80, e-mail 

airworthiness.A330-A340@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. 

TABLE 3—MATERIAL INCORPORATED BY REFERENCE

Airbus Mandatory Service Bulletin Revision Date 

A330–92–3066 ................................................................................................................................................ 01 August 1, 2008. 

A330–92–3066 ................................................................................................................................................ 02 March 19, 2009. 

A340–92–4071 ................................................................................................................................................ 01 August 1, 2008. 

A340–92–4071 ................................................................................................................................................ 02 November 28, 2008. 

A340–92–4071 ................................................................................................................................................ 03 March 19, 2009. 

Issued in Renton, Washington, on July 2, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–16468 Filed 7–14–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0138; Directorate 

Identifier 2008–NM–216–AD; Amendment 

39–15966; AD 2009–15–03] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model BD–700–1A10 and BD–700– 

1A11 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing 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: 

During scheduled maintenance inspection, 

a bolt which connects the PCU (power 

control unit) to the elevator surface was 

found fractured in the assembly. Further 

inspection of the assembly revealed that the 

bearing on the PCU rod end had seized, 

which resulted in damage to the attachment 

fitting bushing and fracture of the bolt. 

Inspection of other in-service airplanes 

revealed two more seized PCU attachment 

joints. However, except seizure, no fractured 

bolt was found on these airplanes. Failure of 

the bolts in both PCUs on one side could 

result in disconnection of the elevator control 

surface which would lead to flutter and loss 

of the aircraft. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

August 19, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 19, 2009. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Pong K. Lee, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE– 

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7324; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on February 23, 2009 (74 FR 

8045). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During scheduled maintenance inspection, 

a bolt which connects the PCU (power 

control unit) to the elevator surface was 

found fractured in the assembly. Further 

inspection of the assembly revealed that the 

bearing on the PCU rod end had seized, 

which resulted in damage to the attachment 

fitting bushing and fracture of the bolt. 

Inspection of other in-service airplanes 

revealed two more seized PCU attachment 

joints. However, except seizure, no fractured 

bolt was found on these airplanes. Failure of 

the bolts in both PCUs on one side could 

result in disconnection of the elevator control 

surface which would lead to flutter and loss 

of the aircraft. 

This Airworthiness Directive (AD) is 

issued to mandate the inspection and 


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