51906 Federal Register / Vol. 73, No. 174 / Monday, September 8, 2008 / Rules and Regulations 

required prior to issuance of the special flight 

permit. Before using any approved special 

flight permits, notify your appropriate 

principal inspector (PI) in the FAA Flight 

Standards District Office (FSDO), or lacking 

a PI, your local FSDO. Special flight permits 

may be permitted provided that the 

conditions specified in paragraphs (m)(1), 

(m)(2), (m)(3), (m)(4), and (m)(5) of this AD 

are met. 

(1) Both the right-hand side and left-hand 

side of the airplane must have at least one 

barrel nut that is not within the suspect batch 

(i.e., barrel nut is not identified with a 

marking of LH7940T SPS 01). The barrel nuts 

that are not within the suspect batch must be 

in good working condition (i.e., no cracking 

of the barrel nut). 

(2) No passengers and no cargo are 

onboard. 

(3) Airplane must operate in fair weather 

conditions with a low risk of turbulence. 

(4) Airplane must operate with reduced 

airspeed. For further information, contact 

Bombardier, Q Series 24 Hour Service 

Customer Response Center, at: Telephone 1–

416–375–4000; fax 1–416–375–4539; E-mail: 

thd.qseries@aero.bombardier.com. 

(5) All of the conditions specified in 

paragraphs (m)(1), (m)(2), (m)(3), and (m)(4) 

of this AD are on a case-by-case basis. 

Contact your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO, for assistance. 

Alternative Methods of Compliance 

(AMOCs) 

(n)(1) The Manager, New York ACO, 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: 

Pong Lee, Aerospace Engineer, Airframe and 

Propulsion Branch, ANE–171, FAA, New 

York ACO, 1600 Stewart Avenue, Suite 410, 

Westbury, New York 11590; telephone (516) 

228–7324; fax (516) 794–5531. 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. 

Related Information 

(o) Canadian airworthiness directive CF–

2008–11R1, dated May 9, 2008, also 

addresses the subject of the AD. 

Material Incorporated by Reference 

(p) You must use Bombardier Alert Service 

Bulletin A84–57–19, Revision A, dated 

February 6, 2008; or Bombardier Alert 

Service Bulletin A84–57–19, Revision B, 

dated March 6, 2008; as applicable; to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Bombardier Alert Service Bulletin A84–57–

19, Revision B, dated March 6, 2008, in 

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

part 51. 

(2) On February 13, 2008 (73 FR 8187, 

February 13, 2008), the Director of the 

Federal Register approved the incorporation 

by reference of Bombardier Alert Service 

Bulletin A84–57–19, Revision A, dated 

February 6, 2008. 

(3) Contact Bombardier, Inc., Bombardier 

Regional Aircraft Division, 123 Garratt 

Boulevard, Downsview, Ontario M3K 1Y5, 

Canada, for a copy of this service 

information. You may review copies at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington; 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 Renton, Washington, on August 

18, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–19718 Filed 9–5–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0672; Directorate 

Identifier 2008–NM–032–AD; Amendment 

39–15660; AD 2008–18–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200, A330–300, and A340–300 

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: 

During manufacturing of A330/A340 

aircraft framework, cracks have been found 

on Frame (FR) 12, left (LH) and right (RH) 

sides. It has been confirmed that a defect of 

the FR12 forming tool press is the root cause 

of the cracks. 

If undetected such damage could affect, 

after propagation, the structural integrity of 

the aircraft. 

* * * * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

October 14, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 14, 2008. 

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 June 24, 2008 (73 FR 35595). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During manufacturing of A330/A340 

aircraft framework, cracks have been found 

on Frame (FR) 12, left (LH) and right (RH) 

sides. It has been confirmed that a defect of 

the FR12 forming tool press is the root cause 

of the cracks. 

If undetected such damage could affect, 

after propagation, the structural integrity of 

the aircraft. 

In order to permit an early detection and 

repair of cracks on FR12, LH and RH sides, 

this Airworthiness Directive (AD) mandates a 

one time High Frequency Eddy Current 

(HFEC) inspection of FR12. 

Corrective actions include, for certain 

findings, contacting Airbus for repair 

instructions and doing the repair; 

repairing cracking (i.e., installing a new 

splice); and applying new protective 

coatings and corrosion inhibitors. 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. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 


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Federal Register / Vol. 73, No. 174 / Monday, September 8, 2008 / Rules and Regulations 51907 

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 

about 20 products of U.S. registry. We 

also estimate that it will take about 3 

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 $4,800, or 

$240 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. 

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: 

2008–18–03 Airbus: Amendment 39–15660. 

Docket No. FAA–2008–0672; Directorate 

Identifier 2008–NM–032–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 14, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A330–

200, A330–300, and A340–300 series 

airplanes; certificated in any category; all 

certified models, all manufacturing serial 

numbers (MSN) from MSN 0489 through 

0722 inclusive, and MSN 0725, 0726, 0728, 

0730, 0732, and 0734. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During manufacturing of A330/A340 

aircraft framework, cracks have been found 

on Frame (FR) 12, left (LH) and right (RH) 

sides. It has been confirmed that a defect of 

the FR12 forming tool press is the root cause 

of the cracks. 

If undetected such damage could affect, 

after propagation, the structural integrity of 

the aircraft. 

In order to permit an early detection and 

repair of cracks on FR12, LH and RH sides, 

this Airworthiness Directive (AD) mandates a 

one time High Frequency Eddy Current 

(HFEC) inspection of FR12. 

Corrective actions include, for certain 

findings, contacting Airbus for repair 

instructions and doing the repair; repairing 

cracking (i.e., installing a new splice); and 

applying new protective coatings and 

corrosion inhibitors. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Prior to the accumulation of 19,500 

total flight cycles or within 3 months after 

the effective date of this AD, whichever 

occurs later: Perform a HFEC inspection at 

the LH and RH sides of frame 12, in 

accordance with the instructions defined in 

Airbus Mandatory Service Bulletin A330–53–

3174 or A340–53–4177, both dated October 

10, 2007, as applicable. If no cracking is 

found, no further action is required by this 

AD. Except as required by paragraph (f)(2) of 

this AD, if any cracking is found, before 

further flight, do the applicable corrective 

actions in accordance with the instructions of 

Airbus Mandatory Service Bulletin A330–53–

3174 or A340–53–4177, as applicable. 

(2) If any cracking is found that exceeds the 

limits specified in Airbus Mandatory Service 

Bulletin A330–53–3174 or A340–53–4177, 

both dated October 10, 2007, as applicable; 

or if any cracking is found during any HFEC 

inspection of the cut-out area; before further 

flight, contact Airbus for repair instructions 

and do the repair. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

difference. 

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 


pwalker on PROD1PC71 with RULES
51908 Federal Register / Vol. 73, No. 174 / Monday, September 8, 2008 / Rules and Regulations 

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 European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2007–0302, dated December 14, 2007; and 

Airbus Mandatory Service Bulletins A330–

53–3174 and A340–53–4177, both dated 

October 10, 2007; for related information. 

Material Incorporated by Reference 

(i) You must use Airbus Mandatory Service 

Bulletin A330–53–3174, including Appendix 

01, dated October 10, 2007; or Airbus 

Mandatory Service Bulletin A340–53–4177, 

including Appendix 01, dated October 10, 

2007; as applicable; 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, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France. 

(3) You may review copies at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; 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 Renton, Washington, on August 

18, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–19720 Filed 9–5–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0407; Directorate 

Identifier 2008–NM–002–AD; Amendment 

39–15662; AD 2008–18–05] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Model 717–200 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

McDonnell Douglas Model 717–200 

airplanes. This AD requires inspecting 

the drive assembly of the aft elevator 

standby loop of the elevator standby 

cable system for interference between 

the clevis and bolt of the bellcrank 

assembly, correct orientation of the pullpull cable clevis bolt, and excessive 

freeplay of the bellcrank assembly 

bearing, and corrective actions if 

necessary. This AD also requires 

modifying the pull-pull cable clevis in 

the drive assembly of the aft elevator 

standby loop for certain airplanes. This 

AD results from a report of an aborted 

takeoff due to a control column 

disconnect. We are issuing this AD to 

prevent binding of the bolt that connects 

the cable 264A clevis to the bellcrank 

assembly against the adjacent (upper) 

clevis of the pull-pull cable assembly. 

This binding condition could result in 

slow airplane rotation or a control 

column disconnect during takeoff and a 

runway excursion if takeoff must be 

aborted. 

DATES: This AD is effective October 14, 

2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 14, 2008. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Long Beach 

Division, 3855 Lakewood Boulevard, 

Long Beach, California 90846; 

Attention: Data and Service 

Management, Dept. C1–L5A (D800–

0024). 

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 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

David Rathfelder, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; telephone (562) 

627–5229; fax (562) 627–5210. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to 

certain McDonnell Douglas Model 717–

200 airplanes. That NPRM was 

published in the Federal Register on 

April 7, 2008 (73 FR 18725). That NPRM 

proposed to require inspecting the drive 

assembly of the aft elevator standby 

loop for interference between the clevis 

and bolt of the bellcrank assembly, 

correct orientation of the pull-pull cable 

clevis bolt, and excessive freeplay of the 

bellcrank assembly bearing, and 

corrective actions if necessary. That 

NPRM also proposed to require 

modifying the pull-pull cable clevis in 

the drive assembly of the aft elevator 

standby loop for certain airplanes. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Change Summary Section 

for Clarification 

Boeing asks that the second sentence 

of the Summary section in the NPRM, 

which describes what is to be inspected, 

be changed as follows: ‘‘This proposed 

AD would require inspecting the aft 

elevator standby loop drive assembly of 

the elevator standby cable system for 

interference between the clevis and bolt 

of this bellcrank assembly, correct 

orientation of the pull-pull cable clevis 

bolt, and excessive freeplay of the 

bellcrank assembly bearing, and 

corrective actions if necessary.’’ Boeing 

states that this would more accurately 

describe the drive assembly being 

inspected since there are two drive 

assemblies in the elevator standby cable 

system. 

We agree that the description in the 

Summary section of the AD should be 

clarified. Therefore, we have changed 

the Summary section and all other 


pwalker on PROD1PC71 with RULES