Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations 13103 

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 Bombardier, Inc., Canadair, 

Aerospace Group, P.O. Box 6087, Station 

Centre-ville, Montreal, Quebec H3C 3G9, 

Canada. 

(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 February 

28, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–4501 Filed 3–11–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–0230; Directorate 

Identifier 2007–NM–043–AD; Amendment 

39–15419; AD 2008–06–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200, A330–300, A340–200, and 

A340–300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to all Airbus Model 

A330–200, A330–300, A340–200, and 

A340–300 series airplanes. That AD 

currently requires an accelerated 

schedule of repetitive testing of the 

elevator servo control loops, and 

corrective actions if necessary. This new 

AD retains the existing requirements, 

reduces the applicability of the existing 

AD, and adds terminating actions. This 

AD results from reports of failed 

elevator servo controls due to broken 

guides. We are issuing this AD to 

prevent failure of the elevator servo 

controls during certain phases of 

takeoff, which could result in an 

unannounced loss of elevator control 

and consequent reduced controllability 

of the airplane. 

DATES: This AD becomes effective April 

16, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of April 16, 2008. 

On November 29, 2005 (70 FR 69065, 

November 14, 2005), the Director of the 

Federal Register approved the 

incorporation by reference of Airbus All 

Operators Telex A330–27A3138, 

Revision 01, dated October 3, 2005; and 

Airbus All Operators Telex A340–

27A4137, Revision 01, dated October 3, 

2005. 

ADDRESSES: For service information 

identified in this AD, contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France. 

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: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington 

98057–3356; telephone (425) 227–2797; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2005–23–10, amendment 

39–14368 (70 FR 69065, November 14, 

2005). The existing AD applies to all 

Airbus Model A330–200, A330–300, 

A340–200, and A340–300 series 

airplanes. That NPRM was published in 

the Federal Register on November 26, 

2007 (72 FR 65906). That NPRM 

proposed to retain the existing 

requirements, reduce the applicability 

of the existing AD, and add terminating 

actions. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment that has been 

received on the NPRM. 

Request To Extend Compliance Time 

for the Modification 

Air Transport Association (ATA) and 

one of its members, Northwest Airlines 

(NWA), state that the terminating action 

specified in the proposed AD should be 

mandated at a maximum of 24 months 

after the effective date for coordination 

with the aircraft C-check intervals. 

NWA adds that the repetitive tests of the 

elevator servo-loops will ensure 

continued safe operation until 

terminating action is accomplished. 

We do not agree with the request from 

ATA and NWA to extend the 

compliance time. In developing an 

appropriate compliance time for this 

action, we considered the urgency 

associated with the subject unsafe 

condition, the availability of required 

parts, and the practical aspect of 

accomplishing the required 

modification within a period of time 

that corresponds to the normal 

scheduled maintenance for most 

affected operators. In light of these 

items, we have determined that a 17- 

month compliance time is appropriate. 

However, according to the provisions of 

paragraph (q) of the AD, we may 

approve requests to adjust the 

compliance time if the request includes 

data that justify that the new 

compliance time would provide an 

acceptable level of safety. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

that has been submitted, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators of the 

affected Model A330–200 and A330–

300 series airplanes to comply with this 

AD. 


jlentini on PROD1PC65 with RULES
13104 Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations 

ESTIMATED COSTS

Action Work 

hour(s) 

Average 

labor rate 

per hour 

Parts Cost per 

airplane 

Number of 

U.S.- 

registered airplanes 

Fleet cost 

Inspection (required by AD 2005–

23–10).

1 $80 None ................. $80, per inspection 

cycle. 

18 $1,440, per inspection cycle. 

Modifications (new actions) .......... 28 80 The manufacturer states 

that it will supply required 

parts to the 

operators at 

no cost.

$2,240 18 $40,320. 

Currently, there are no affected Model 

A340–200 and A340–300 series 

airplanes on the U.S. Register. However, 

if an affected airplane is imported and 

placed on the U.S. Register in the future, 

the modification would take about 10 

work hours, at an average labor rate of 

$80 per work hour. The manufacturer 

states that it will supply required parts 

to the operators at no cost. Based on 

these figures, we estimate the cost of 

this AD for Model A340–200 and A340–

300 series airplanes to be $800 per 

airplane. 

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 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 

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. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–14368 (70 

FR 69065, November 14, 2005), and by 

adding the following new airworthiness 

directive (AD): 

2008–06–07 Airbus: Amendment 39–15419. 

Docket No. FAA–2007–0230; Directorate 

Identifier 2007–NM–043–AD. 

Effective Date 

(a) This AD becomes effective April 16, 

2008. 

Affected ADs 

(b) This AD supersedes AD 2005–23–10. 

Applicability 

(c) This AD applies to the airplanes 

identified in Table 1 of this AD, certificated 

in any category. 

TABLE 1.—APPLICABILITY

Airbus model— Excluding those airplanes on which any of the following— Has been installed—

A330–200, A330–300, A340–200, and 

A340–300 series airplanes.

Airbus modification 54833 .................................................................................... In production. 

Airbus Service Bulletin A330–27–3136, Revision 01, dated July 19, 2006 ........ In service. 

Airbus Service Bulletin A340–27–4135, dated January 12, 2006 ....................... In service. 

Unsafe Condition 

(d) This AD results from reports of failed 

elevator servo controls due to broken guides. 

We are proposing this AD to prevent failure 

of the elevator servo controls during certain 

phases of takeoff, which could result in an 

unannounced loss of elevator control and 

consequent reduced controllability of the 

airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 


jlentini on PROD1PC65 with RULES
Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations 13105 

the compliance times specified, unless the 

actions have already been done. 

Requirements of AD 2005–23–10: 

Service Information 

(f) The term ‘‘AOT,’’ as used in paragraphs 

(g) through (i) of this AD, means section 4.2. 

‘‘Description’’ of the following service 

information, as applicable: 

(1) For Model A330–200 and –300 series 

airplanes: Airbus All Operators Telex A330–

27A3138, Revision 01, dated October 3, 2005; 

and 

(2) For Model A340–200 and –300 series 

airplanes: Airbus All Operators Telex A340–

27A4137, Revision 01, dated October 3, 2005. 

Initial and Repetitive Elevator Servo-Loop 

Tests 

(g) Within 200 flight hours after November 

29, 2005 (the effective date of AD 2005–23–

10): Test the elevator servo-loops, in 

accordance with the AOT, except as provided 

by paragraph (j) of this AD. If the test of the 

elevator servo-loops passes, repeat the test at 

intervals not to exceed 140 flight hours or 8 

days, whichever occurs first. 

Failed Tests 

(h) If any test of the elevator servo-loops 

required by paragraph (g) of this AD fails: 

Before further flight, troubleshoot the cause 

of the test failure, and do the applicable 

corrective actions; in accordance with the 

AOT, except as provided by paragraph (j) of 

this AD. Thereafter, repeat the test at the 

times specified in paragraph (g) of this AD. 

Reporting Requirement 

(i) Following each test required by 

paragraph (g) of this AD, submit a report of 

the findings of only failed elevator servo-loop 

tests to Airbus Customer Services, 

Engineering and Technical Support, 

Attention: Mr. J. Laurent, SEE53, fax +33/ 

(0)5.61.93.44.25; at the applicable time 

specified in paragraph (i)(1) or (i)(2) of this 

AD. The report must include the description 

of the failure experienced during the test, the 

identified cause of the failure, and the 

number of flight hours and flight cycles on 

the airplane. Under the provisions of the 

Paperwork Reduction Act of 1980 (44 U.S.C. 

3501 et seq.), the Office of Management and 

Budget (OMB) has approved the information 

collection requirements contained in this AD 

and has assigned OMB Control Number 

2120–0056. 

(1) If the test was done after November 29, 

2005: Submit the report within 10 days after 

the test. 

(2) If the test was done prior to November 

29, 2005: Submit the report within 10 days 

after November 29, 2005. 

New Requirements of This AD 

New Service Information for Testing 

(j) As of the effective date of this AD, do 

the actions required by paragraphs (g) and (h) 

of this AD in accordance with the 

Accomplishment Instructions of the 

following service bulletins, as applicable. 

(1) For Model A330–200 and –300 series 

airplanes: Airbus Service Bulletin A330–27–

3138, Revision 02, excluding Appendix 01, 

dated May 30, 2006; and 

(2) For Model A340–200 and –300 series 

airplanes: Airbus Service Bulletin A340–27–

4137, Revision 02, excluding Appendix 01, 

dated May 30, 2006. 

Terminating Actions 

(k) Within 17 months after the effective 

date of this AD, modify the four elevator 

servo controls in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–27–3136, Revision 01, 

dated July 19, 2006 (for Model A330–200 and 

–300 series airplanes); or Airbus Service 

Bulletin A340–27–4135, dated January 12, 

2006 (for Model A340–200 and –300 series 

airplanes); as applicable. 

Note 1: Airbus Service Bulletins A330–27–

3136 and A340–27–4135 refer to Goodrich 

Actuation Systems Service Bulletin SC4800–

27–18, Revision 1, dated May 19, 2006, as an 

additional source of service information for 

accomplishing the modification required by 

paragraph (k) of this AD. 

(l) Modifications done before the effective 

date of this AD in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–27–3136, dated 

January 12, 2006, are acceptable for 

compliance with the modification required 

by paragraph (k) of this AD. 

(m) Concurrently with the modification 

required by paragraph (k) of this AD, modify 

the four elevator servo controls in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A330–27–3134, 

Revision 01, dated May 12, 2006 (for Model 

A330–200 and –300 series airplanes); or 

Airbus Service Bulletin A340–27–4132, 

dated October 13, 2005 (for Model A340–200 

and –300 series airplanes); as applicable. 

Note 2: Airbus Service Bulletins A330–27–

3134 and A340–27–4132 refer to Goodrich 

Actuation Systems Service Bulletin SC4800–

27–17, Revision 2, dated May 19, 2006, as an 

additional source of service information for 

accomplishing the modification required by 

paragraph (m) of this AD. 

(n) Modifications done before the effective 

date of this AD in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–27–3134, dated 

October 13, 2005, are acceptable for 

compliance with the modification required 

by paragraph (m) of this AD. 

(o) Accomplishment of the modifications 

required by paragraphs (k) and (m) of this AD 

constitutes terminating action for the 

requirements of paragraphs (f) through (i) of 

this AD. 

Parts Installation 

(p) As of the effective date of this AD, no 

person may install, on any airplane, an 

elevator servo control, unless it has been 

modified in accordance with paragraphs (k) 

and (m) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(q)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. 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 

(r) European Aviation Safety Agency 

airworthiness directive 2007–0008, dated 

January 9, 2007, also addresses the subject of 

this AD. 

Material Incorporated by Reference 

(s) You must use the applicable Airbus 

service information contained in Table 2 of 

this AD to perform the actions that are 

required by this AD, unless the AD specifies 

otherwise. 

TABLE 2.—ALL MATERIAL INCORPORATED BY REFERENCE

Service information Revision Date 

Airbus All Operators Telex A330–27A3138 ..................................................................................................... 01 ................ October 3, 2005. 

Airbus All Operators Telex A340–27A4137 ..................................................................................................... 01 ................ October 3, 2005. 

Airbus Service Bulletin A330–27–3134 ........................................................................................................... 01 ................ May 12, 2006. 

Airbus Service Bulletin A330–27–3136 ........................................................................................................... 01 ................ July 19, 2006. 

Airbus Service Bulletin A330–27–3138, excluding Appendix 01 .................................................................... 02 ................ May 30, 2006. 

Airbus Service Bulletin A340–27–4132 ........................................................................................................... Original ........ October 13, 2005. 

Airbus Service Bulletin A340–27–4135 ........................................................................................................... Original ........ January 12, 2006. 

Airbus Service Bulletin A340–27–4137, excluding Appendix 01 .................................................................... 02 ................ May 30, 2006. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in Table 3 

of this AD in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. 


jlentini on PROD1PC65 with RULES
13106 Federal Register / Vol. 73, No. 49 / Wednesday, March 12, 2008 / Rules and Regulations 

TABLE 3.—ALL MATERIAL INCORPORATED BY REFERENCE

Service information Revision Date 

Airbus Service Bulletin A330–27–3134 ........................................................................................................... 01 ................ May 12, 2006. 

Airbus Service Bulletin A330–27–3136 ........................................................................................................... 01 ................ July 19, 2006. 

Airbus Service Bulletin A330–27–3138, excluding Appendix 01 .................................................................... 02 ................ May 30, 2006. 

Airbus Service Bulletin A340–27–4132 ........................................................................................................... Original ........ October 13, 2005. 

Airbus Service Bulletin A340–27–4135 ........................................................................................................... Original ........ January 12, 2006. 

Airbus Service Bulletin A340–27–4137, excluding Appendix 01 .................................................................... 02 ................ May 30, 2006. 

(2) On November 29, 2005 (70 FR 69065, 

November 14, 2005), the Director of the 

Federal Register approved the incorporation 

by reference of Airbus All Operators Telex 

A330–27A3138, Revision 01, dated October 

3, 2005; and Airbus All Operators Telex 

A340–27A4137, Revision 01, dated October 

3, 2005. 

(3) For service information identified in 

this AD, contact Airbus, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France. 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 March 3, 

2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–4671 Filed 3–11–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–0368; Directorate 

Identifier 2007–NM–050–AD; Amendment 

39–15420; AD 2008–06–08] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited Model 

BAe 146–100A, –200A, and –300A 

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: 

Cracking has been found on the centre 

fuselage top aft longeron at Rib ‘0’ on an inservice aircraft. * * * 

This condition could result in reduced 

structural integrity of the airplane. We 

are issuing this AD to require actions to 

correct the unsafe condition on these 

products. 

DATES: This AD becomes effective April 

16, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 16, 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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1175; 

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 December 20, 2007 (72 FR 

72270). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Cracking has been found on the centre 

fuselage top aft longeron at Rib ‘0’ on an inservice aircraft. Subsequent investigation has 

indicated that the currently defined 

threshold and repeat inspection period must 

be reduced, and the area of inspection 

expanded for the BAe 146 series 100 and 200. 

For the BAe146 series 300, only the repeat 

inspection period must be reduced, and the 

area of inspection expanded. 

Cracking on the center fuselage top aft 

longeron at Rib ‘0,’ could result in 

reduced structural integrity of the 

airplane. Corrective actions include 

repetitive inspections of the center 

fuselage top aft longeron for cracking 

and repair/replacement if necessary. 

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. 

Revision to the Reference to the 

Nondestructive Testing (NDT) Manual 

We have removed the reference to the 

BAE Systems (Operations) Limited BAe 

146/Avro 146–RJ Series NDT Manual 

Part 6 20–00–03 from paragraphs 

(f)(2)(iii) and (f)(5)(iii) of this AD. The 

appropriate source of service 

information for doing the inspection 

and repair specified in paragraphs 

(f)(2)(iii) and (f)(5)(iii) of this AD is BAE 

Systems (Operations) Limited 

Inspection Service Bulletin ISB.53–173, 

Revision 2, dated March 28, 2006. The 

Accomplishment Instructions of the 

service bulletin refer to the NDT 

manual. We have added Note 1 and 

Note 3 to this AD to clarify that the 

service bulletin refers to the NDT 

manual as a secondary source of service 

information for doing the inspection. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

with the change 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. 


jlentini on PROD1PC65 with RULES