56454 Federal Register / Vol. 73, No. 189 / Monday, September 29, 2008 / Rules and Regulations 

may be done by inserting a copy of this AD 

in the AFM. 

Note 1: When a statement to prohibit 

application of brakes during backward 

movement of the airplane has been included 

in the general revisions of the AFM, the 

general revisions may be inserted into the 

AFM, and the copy of this AD may be 

removed from the AFM. 

(g) Within 14 days after April 26, 2006, 

affix a placard on the pedestal, next to the 

parking brake handle, having the following 

wording: ‘‘APPLICATION OF BRAKES 

DURING BACKWARD MOVEMENT IS 

PROHIBITED.’’ 

Inspection and Corrective Action 

(h) At the applicable time specified in 

paragraph (h)(1) or (h)(2) of this AD: Do an 

eddy current inspection of the MLG main 

fittings and repair before further flight as 

applicable, in accordance with the 

Accomplishment Instructions of MessierDowty Service Bulletin F100–32–106, 

including Appendices A through C and 

excluding Appendix D, dated February 18, 

2005, except as provided by paragraphs (i) 

and (j) of this AD. 

(1) For airplanes on which an inspection 

has not been done in accordance with 

Messier-Dowty Service Bulletin F100–32– 

104, Revision 2, dated October 30, 2003: 

Within 3 months after April 26, 2006. 

(2) For airplanes on which an inspection 

has been done in accordance with MessierDowty Service Bulletin F100–32–104, 

Revision 2, dated October 30, 2003: Within 

2,000 flight cycles since the last inspection 

done in accordance with the service bulletin 

or within 3 months after April 26, 2006, 

whichever occurs later. 

Exceptions to the Service Bulletin 

(i) Where Messier-Dowty Service Bulletin 

F100–32–106, including Appendices A 

through C and excluding Appendix D, dated 

February 18, 2005, specifies contacting the 

manufacturer for repair: Before further flight, 

repair using a method approved by either the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

Civil Aviation Authority—The Netherlands 

(CAA–NL) (or its delegated agent). 

(j) Although Messier-Dowty Service 

Bulletin F100–32–106, including Appendices 

A through C and excluding Appendix D, 

dated February 18, 2005, specifies to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

Parts Installation 

(k) As of April 26, 2006, and until the 

effective date of this AD, no person may 

install, on any airplane, a Messier-Dowty 

MLG, unless it has been inspected/repaired 

according to paragraph (h) of this AD. 

New Requirements of This AD 

Inspection and Repair 

(l) At the applicable times specified in 

paragraphs (l)(1), (l)(2), and (l)(3) of this AD: 

Do an eddy current inspection of the MLG 

main fitting for cracks, and rework the MLG 

main fitting if applicable, in accordance with 

the Accomplishment Instructions of MessierDowty Service Bulletin F100–32–111, 

including Appendices A through C and 

excluding Appendix D, dated December 20, 

2005; except as provided by paragraph (m) of 

this AD. The rework must be done before 

further flight. 

(1) For all MLG main fittings, except those 

units identified in paragraph (l)(2) of this AD: 

Inspect within the next 2,000 flight cycles 

since the last inspection required by 

paragraph (h) of this AD, or within 4 months 

after the effective date of this AD, whichever 

occurs later. 

(2) For new MLG main fittings and MLG 

main fittings on which both bores have been 

repaired (reworked) in accordance with 

paragraph (h) of this AD: Inspect within 

4,000 flight cycles since new (installation) or 

repaired (rework) in accordance with 

paragraph (h) of this AD, as applicable. 

(3) For all MLGs: Repeat the eddy current 

inspection thereafter at intervals not to 

exceed 2,000 flight cycles. 

Exception to Service Bulletin F100–32–111 

(m) Although Messier-Dowty Service 

Bulletin F100–32–111, including Appendices 

A through C and excluding Appendix D, 

dated December 20, 2005, specifies to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

Parts Installation 

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

person may install, on any airplane, a 

Messier-Dowty MLG, unless it has been 

inspected and reworked in accordance with 

paragraph (l) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(o) The Manager, International Branch, 

ANM–116, 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: Tom Rodriguez, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1137; 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. 

Related Information 

(p) Dutch airworthiness directive NL– 

2006–003, dated February 7, 2006, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(q) You must use Messier-Dowty Service 

Bulletin F100–32–106, including Appendices 

A through C and excluding Appendix D, 

dated February 18, 2005; and Messier-Dowty 

Service Bulletin F100–32–111, including 

Appendices A through C and excluding 

Appendix D, dated December 20, 2005; 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 

Messier-Dowty Service Bulletin F100–32– 

111, including Appendices A through C and 

excluding Appendix D, dated December 20, 

2005, in accordance with 5 U.S.C. 552(a) and 

1 CFR part 51. 

(2) On April 26, 2006 (71 FR 14363, March 

22, 2006), the Director of the Federal Register 

approved the incorporation by reference of 

Messier-Dowty Service Bulletin F100–32– 

106, including Appendices A through C and 

excluding Appendix D, dated February 18, 

2005. 

(3) Contact Fokker Services B.V., Technical 

Services Dept., P.O. Box 231, 2150 AE 

Nieuw-Vennep, the Netherlands, for a copy 

of this service information. 

(4) 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 

September 11, 2008. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–22210 Filed 9–26–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0636; Directorate 

Identifier 2007–NM–324–AD; Amendment 

39–15657; AD 2008–17–19] 

RIN 2120–AA64 

Airworthiness Directives; ATR Model 

ATR42–200, –300, and –320 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: 

One ATR 42–300 experienced a collapse of 

the Right (RH) Main Landing Gear (MLG) 

when taxiing, caused by failure of the side 

brace assembly. Investigations revealed a 

crack propagation that occurred from a 

corrosion pit, in a very high stressed area of 

the upper arm. * * * 

* * * * * 

The unsafe condition is cracking of the 

upper arms of the secondary side brace 

assemblies of the MLG, which could 

result in collapse of the MLG during 


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Federal Register / Vol. 73, No. 189 / Monday, September 29, 2008 / Rules and Regulations 56455 

takeoff or landing, damage to the 

airplane, and possible injury to the 

flightcrew and passengers. We are 

issuing this AD to require actions to 

correct the unsafe condition on these 

products. 

DATES: This AD becomes effective 

November 3, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 3, 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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1137; 

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 10, 2008 (73 FR 32659). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

One ATR 42–300 experienced a collapse of 

the Right (RH) Main Landing Gear (MLG) 

when taxiing, caused by failure of the side 

brace assembly. Investigations revealed a 

crack propagation that occurred from a 

corrosion pit, in a very high stressed area of 

the upper arm. Dimensions of the corrosion 

pit were lower than the minimum defect size 

that can be detected by usual inspection 

means used during landing gear overhaul. 

The superseded EASA (European Aviation 

Safety Agency) Airworthiness Directive (AD) 

2007–0112 was issued to require repetitive 

inspections on affected high stressed areas on 

MLG side brace assemblies for crack 

detection and to replace the affected side 

brace assembly if any defect was found. 

Since the issuance of [EASA] AD 2007– 

0112, a modification of [the] side brace upper 

arm has been developed as terminating 

action. However, production non-conformity 

of the inspection tool was discovered. 

In order to correct the discrepancy of the 

initial tool, new inspection tool components 

have been manufactured and the Service 

Bulletin (SB) Messier Dowty 631–32–191 has 

been updated to revision 2 accordingly. This 

directive mandates re-inspection of MLG side 

brace assemblies previously inspected [in 

accordance with] revision 1 of the Messier 

Dowty SB 631–32–191 and reduces the 

inspection interval initially proposed in 

[EASA] AD 2007–0112 in order to maintain 

the same level of confidence. 

* * * * * 

The unsafe condition is cracking of the 

upper arms of the secondary side brace 

assemblies of the MLG, which could 

result in collapse of the MLG during 

takeoff or landing, damage to the 

airplane, and possible injury to the 

flightcrew and passengers. 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 

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 31 products of U.S. registry. We 

also estimate that it will take about 35 

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. Based on these figures, we 

estimate the cost of this AD to the U.S. 

operators to be $86,800, or $2,800 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. 

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: 


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56456 Federal Register / Vol. 73, No. 189 / Monday, September 29, 2008 / Rules and Regulations 

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: 

2008–17–19 ATR—Gie Avions De 

Transport Re ́gional (Formerly 

Aerospatiale): Amendment 39–15657. 

Docket No. FAA–2008–0636; Directorate 

Identifier 2007–NM–324–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 3, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to ATR Model ATR42– 

200, –300, and –320 airplanes, certificated in 

any category; excluding airplanes on which 

ATR Modification 8463 has been done. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

One ATR 42–300 experienced a collapse of 

the Right (RH) Main Landing Gear (MLG) 

when taxiing, caused by failure of the side 

brace assembly. Investigations revealed a 

crack propagation that occurred from a 

corrosion pit, in a very high stressed area of 

the upper arm. Dimensions of the corrosion 

pit were lower than the minimum defect size 

that can be detected by usual inspection 

means used during landing gear overhaul. 

The superseded EASA (European Aviation 

Safety Agency) Airworthiness Directive (AD) 

2007–0112 was issued to require repetitive 

inspections on affected high stressed areas on 

MLG side brace assemblies for crack 

detection and to replace the affected side 

brace assembly if any defect was found. 

Since the issuance of [EASA] AD 2007– 

0112, a modification of [the] side brace upper 

arm has been developed as terminating 

action. However, production non-conformity 

of the inspection tool was discovered. 

In order to correct the discrepancy of the 

initial tool, new inspection tool components 

have been manufactured and the Service 

Bulletin (SB) Messier Dowty 631–32–191 has 

been updated to revision 2 accordingly. This 

directive mandates re-inspection of MLG side 

brace assemblies previously inspected [in 

accordance with] revision 1 of the Messier 

Dowty SB 631–32–191 and reduces the 

inspection interval initially proposed in 

[EASA] AD 2007–0112 in order to maintain 

the same level of confidence. 

* * * * * 

The unsafe condition is cracking of the upper 

arms of the secondary side brace assemblies 

of the MLG, which could result in collapse 

of the MLG during takeoff or landing, damage 

to the airplane, and possible injury to the 

flightcrew and passengers. 

Actions and Compliance 

(f) For MLG side brace assemblies with part 

number (P/N) D22710000, without suffix ‘‘– 

9’’: Unless already done, do the following 

actions. 

(1) For airplanes on which the MLG side 

brace assemblies have not been inspected as 

of the effective date of this AD, in accordance 

with the Accomplishment Instructions of 

Messier-Dowty Service Bulletin 631–32–191, 

Revision 1, dated February 26, 2007: Perform 

the initial eddy current inspection for 

cracking of the MLG side brace, in 

accordance with the Accomplishment 

Instructions of Messier-Dowty Special 

Inspection Service Bulletin 631–32–191, 

Revision 2, dated August 30, 2007, at the 

applicable time specified in Table 1 of this 

AD. Unless otherwise specified, the flight 

cycles and times indicated in Table 1 of this 

AD must be interpreted as total flight cycles 

since overhaul, or time since overhaul, and 

as total flight cycles since new or time since 

manufacture for side brace assemblies that 

have not undergone any overhaul yet. 

TABLE 1—COMPLIANCE TIMES

For a MLG side brace assembly with the total flight cycles since new or 

total flight cycles since overhaul specified below as of the effective date 

of this AD— 

Do the initial inspection at the time specified below— 

More than 8,000 flight cycles ................................................................... Within 500 flight cycles after the effective date of this AD. 

5,000 or more total flight cycles, but not more than 8,000 total flight cycles.Within 1,000 flight cycles after the effective date of this AD or before 

accumulating 8,500 flight cycles, whichever occurs first. 

Less than 5,000 flight cycles .................................................................... Within 2,000 flight cycles after the effective date of this AD or before 

accumulating 6,000 flight cycles, whichever occurs first. 

(2) For airplanes on which the MLG side 

brace assemblies have been inspected as of 

the effective date of this AD, in accordance 

with the Accomplishment Instructions of 

Messier-Dowty Service Bulletin 631–32–191, 

Revision 1, dated February 26, 2007: Within 

1,000 flight cycles after the last inspection or 

within 200 flight cycles after the effective 

date of this AD, whichever occurs later, 

perform an eddy current inspection for 

cracking of the MLG side brace, in 

accordance with the Accomplishment 

Instructions of Messier-Dowty Special 

Inspection Service Bulletin 631–32–191, 

Revision 2, dated August 30, 2007. 

(3) After accomplishment of the inspection 

required by paragraph (f)(1) or (f)(2) of this 

AD, repeat the inspection at intervals not to 

exceed 2,600 flight cycles in accordance with 

the Accomplishment Instructions of MessierDowty Special Inspection Service Bulletin 

631–32–191, Revision 2, dated August 30, 

2007. 

(4) If any crack is found during any 

inspection required by paragraphs (f)(1), (f)(2) 

and (f)(3) of this AD, before further flight, 

replace the affected side brace in accordance 

with the Accomplishment Instructions of 

Messier-Dowty Special Inspection Service 

Bulletin 631–32–191, Revision 2, dated 

August 30, 2007. 

(5) At the applicable time specified in 

paragraph (f)(5)(i) or (f)(5)(ii) of this AD: 

Inspect for cracking, corrosion, and defects of 

the MLG side brace assemblies with P/N 

D22710000, without suffix ‘‘–9’’, in 

accordance with the Accomplishment 

Instructions of Messier-Dowty Service 

Bulletin 631–32–194, dated June 6, 2007. 

(i) For airplanes having side brace 

assemblies on which Messier-Bugatti Service 

Bulletin 631–32–072 has not been 

incorporated: Before accumulating 16,000 

total flight cycles or within 8 years after the 

effective date of this AD, whichever occurs 

first. 

(ii) For airplanes having side brace 

assemblies on which Messier-Bugatti Service 

Bulletin 631–32–072 has been incorporated: 

Before accumulating 19,000 total flight cycles 

or within 8 years after the effective date of 

this AD, whichever occurs first. 

(6) If no cracking, corrosion, or defect is 

found during any inspection required by 

paragraph (f)(5) of this AD, before further 

flight, modify and re-identify (by adding a 

suffix ‘‘–9’’ to P/N D22710000) the MLG side 

brace assemblies in accordance with the 

Accomplishment Instructions of ATR Service 

Bulletin ATR42–32–0092, dated June 25, 

2007. 

(7) If any cracking, corrosion, or defect is 

found during any inspection required by 

paragraph (f)(5) of this AD, before further 

flight, replace the discrepant MLG side brace 

assembly with a modified and re-identified 

MLG side brace assembly in accordance with 

the Accomplishment Instructions of ATR 

Service Bulletin ATR42–32–0092, dated June 

25, 2007. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: Although 

the MCAI or service information allows 

further flight if a crack is found during 

compliance with the required inspections, 


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Federal Register / Vol. 73, No. 189 / Monday, September 29, 2008 / Rules and Regulations 56457 

this AD requires that you repair the crack 

before further flight. 

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: Tom Rodriguez, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1137; 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 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 EASA Airworthiness 

Directive 2007–0263, dated October 3, 2007, 

and the service information specified in 

Table 2 of this AD, for related information. 

TABLE 2—SERVICE INFORMATION

Service Bulletin Revision Date 

ATR Service Bulletin ATR42–32–0092 .................................................................................................. Original .................. June 25, 2007. 

ATR Technical Instruction ATR42, ATR42–07–01 ................................................................................. Original .................. February 5, 2007. 

Messier-Dowty Service Bulletin 631–32–194 ......................................................................................... Original .................. June 6, 2007. 

Messier-Dowty Special Inspection Service Bulletin 631–32–191 .......................................................... 2 ............................. August 30, 2007. 

Material Incorporated by Reference 

(i) You must use the service information 

specified in Table 3 of this AD to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

TABLE 3—MATERIAL INCORPORATED BY REFERENCE

Service Bulletin Revision Date 

ATR Service Bulletin ATR42–32–0092 .................................................................................................. Original .................. June 25, 2007. 

Messier-Dowty Service Bulletin 631–32–194 ......................................................................................... Original .................. June 6, 2007. 

Messier-Dowty Special Inspection Service Bulletin 631–32–191 .......................................................... 2 ............................. August 30, 2007. 

Messier-Dowty Special Inspection Service 

Bulletin 631–32–191, Revision 2, dated 

August 30, 2007, contains the following 

effective pages: 

Page No. Revision level 

shown on page Date shown on page 

1, 3, 8 .................................................................................................................................................... 2 ............................. August 30, 2007. 

2, 6, 7, 9, 10 .......................................................................................................................................... 1 ............................. February 26, 2007. 

4, 5 ........................................................................................................................................................ Original .................. December 13, 2006. 

(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 ATR, 316 Route de Bayonne, 

31060 Toulouse, Cedex 03, 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 

12, 2008. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–19365 Filed 9–26–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–0078; Directorate 

Identifier 2007–NE–40–AD; Amendment 39– 

15683; AD 2008–20–04] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211 Series Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 


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