Federal Register / Vol. 73, No. 175 / Tuesday, September 9, 2008 / Rules and Regulations 52203 

balance land for cracks in accordance with 

Rolls-Royce RB211 Propulsion System Alert 

Non Modification Service Bulletin RB.211–

72–AF313, dated February 22, 2007 section 

3 Accomplishment Instructions. Engines on 

which cracking is found should be rejected 

from service. 

Inspection—In-Shop 

(2) Applicable to RR Trent 500, 700 and 

800 engines at each shop visit in which the 

engine is sufficiently disassembled to access 

the IP Compressor Module rear face: Inspect 

the IP Compressor rotor rear balance land for 

cracks in accordance with Rolls-Royce RB211 

Propulsion System Alert Non Modification 

Service Bulletin RB.211–72–AF260, Revision 

2, dated July 4, 2007; or earlier issue section 

3 Accomplishment Instructions. 

Other FAA AD Provisions 

(f) 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 

(g) Refer to EASA Airworthiness Directive 

2007–0052, dated February 23, 2007, for 

related information. 

(h) 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 

(i) You must use the service information 

specified in Table 1 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 Rolls-Royce plc, P.O. Box 

31, Derby, DE24 8BJ, United Kingdom; 

telephone: 44 (0) 1332–242424; fax: 44 (0) 

1332–249936. 

(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. 

TABLE 1—MATERIAL INCORPORATED BY REFERENCE

Alert Service Bulletin No. Page Revision Date 

RB.211–72–AF260; Total pages—11 .................................. ALL ....................................... Original ................................. October 17, 2006. 

RB.211–72–AF260; Total pages—11 .................................. ALL ....................................... 1 ............................................ January 17, 2007. 

RB.211–72–AF260; Total pages—11 .................................. ALL ....................................... 2 ............................................ July 4, 2007. 

RB.211–72–AF313; Total pages—11 .................................. ALL ....................................... Original ................................. February 22, 2007. 

Issued in Burlington, Massachusetts, on 

August 25, 2008. 

Mark A. Rumizen, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–20212 Filed 9–8–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0946; Directorate 

Identifier 2008–NM–147–AD; Amendment 

39–15667; AD 2008–18–10] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Model MD–90–30 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

McDonnell Douglas Model MD–90–30 

airplanes. This AD requires a detailed 

inspection for certain defects of the 

upper fasteners of the aft mount support 

fitting of the left and right engines and 

corrective actions if necessary. This AD 

results from reports of loose, cracked, or 

missing fasteners in the aft mount 

support fitting of the left and right 

engines. We are issuing this AD to 

detect and correct loose, cracked, or 

missing fasteners in the engine aft 

support mount fitting, which could lead 

to separation of the support fitting from 

the pylon, which could result in 

separation of the engine from the 

airplane. 

DATES: This AD is effective September 

24, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 24, 2008. 

We must receive comments on this 

AD by November 10, 2008. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M–

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M–

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

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 street address for 

the Docket Office (telephone 800–647–

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Roger Durbin, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; telephone (562) 

627–5233; fax (562) 627–5210. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We have received reports of loose, 

cracked, or missing fasteners in the aft 

mount support fitting of the left and 

right engines on several McDonnell 

Douglas Model MD–90–30 airplanes. 

The airplanes had accumulated between 

18,767 and 25,400 total flight hours and 

between 15,841 and 27,000 total flight 

cycles. A safety assessment of the 

missing fasteners has concluded that 

loose or discrepant fasteners in the top 


yshivers on PROD1PC62 with RULES
52204 Federal Register / Vol. 73, No. 175 / Tuesday, September 9, 2008 / Rules and Regulations 

horizontal row, common with the pylon 

skin, significantly decrease the margin 

of safety of the aft mount support 

installation at the design limit load. 

Loose, cracked, or missing fasteners in 

the engine aft mount support fitting 

could lead to separation of the support 

fitting from the pylon. This condition, if 

not corrected, could result in separation 

of the engine from the airplane. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin MD90–54A002, dated August 1, 

2008. The service bulletin describes 

procedures for doing a detailed 

inspection for certain defects of the 

upper fasteners of the aft mount support 

fitting of the left and right engines, and 

corrective action as applicable. The 

detailed inspection consists of the 

following actions: (1) A general visual 

inspection of the upper fasteners for any 

missing, loose, or damaged fasteners, (2) 

a gap check between the washers and 

structure or between the fastener heads 

and structure, if applicable, and (3) a 

torque check of the fastener nuts, if 

applicable. The corrective action 

includes replacing all fasteners if any 

defect is found. 

FAA’s Determination and Requirements 

of This AD 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the(se) 

same type design(s). This AD requires 

accomplishing the actions specified in 

the service information described 

previously. 

Interim Action 

This is considered to be interim 

action until final action is identified, at 

which time we might consider further 

rulemaking. 

FAA’s Justification and Determination 

of the Effective Date 

Loose, cracked, or missing fasteners in 

the engine aft mount support fitting 

could lead to separation of the support 

fitting from the pylon, possibly resulting 

in separation of the engine from the 

airplane. Because of our requirement to 

promote safe flight of civil aircraft and 

thus, the critical need to assure 

structural integrity of the engine aft 

mount support fitting and the short 

compliance time involved with this 

action, this AD must be issued 

immediately. 

Because an unsafe condition exists 

that requires the immediate adoption of 

this AD, we find that notice and 

opportunity for prior public comment 

hereon are impracticable and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA–

2008–0946; Directorate Identifier 2008–

NM–147–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this AD. We will consider all 

comments received by the closing date 

and may amend this AD because of 

those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2008–18–10 McDonnell Douglas: 

Amendment 39–15667. Docket No. 

FAA–2008–0946; Directorate Identifier 

2008–NM–147–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective September 24, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to McDonnell Douglas 

Model MD–90–30 airplanes, certificated in 

any category; as identified in Boeing Alert 

Service Bulletin MD90–54A002, dated 

August 1, 2008. 

Unsafe Condition 

(d) This AD results from reports of loose, 

cracked, or missing fasteners in the aft mount 

support fitting of the left and right engines. 

We are issuing this AD to detect and correct 

loose, cracked, or missing fasteners in the 

engine aft support mount fitting, which could 

lead to separation of the support fitting from 

the pylon, which could result in separation 

of the engine from the airplane. 

Compliance 

(e) Comply with this AD within the 

compliance times specified, unless already 

done. 

Detailed Inspection 

(f) Within 703 flight cycles after the 

effective date of this AD, do a detailed 


yshivers on PROD1PC62 with RULES
Federal Register / Vol. 73, No. 175 / Tuesday, September 9, 2008 / Rules and Regulations 52205 

inspection for any defect (missing, loose, or 

damaged fasteners; incorrect gap between 

washers and structure or between fastener 

heads and structure; or incorrect torque of 

fastener nuts) of the upper fasteners of the aft 

mount support fitting of the left and right 

engines, and do all the applicable corrective 

actions before further flight, by 

accomplishing all of the applicable actions 

specified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD90–54A002, dated August 1, 2008. 

Credit for Actions Done per Multiple 

Operator Message (MOM) 

(g) Actions done before the effective date 

of this AD in accordance with Boeing MOM 

1–893882781–2, dated July 25, 2008, are 

acceptable for compliance with the 

requirements of paragraph (f) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Los Angeles 

Certification Office (ACO), FAA, ATTN: 

Roger Durbin, Aerospace Engineer, Airframe 

Branch, ANM–120L, FAA, Los Angeles ACO, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; telephone (562) 627–

5233; fax (562) 627–5210; has the authority 

to approve AMOCs for this AD, if requested 

using 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Material Incorporated by Reference 

(i) You must use Boeing Alert Service 

Bulletin MD90–54A002, dated August 1, 

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 Boeing Commercial 

Airplanes, Long Beach Division, 3855 

Lakewood Boulevard, Long Beach, California 

90846, Attention: Data and Service 

Management, Dept. C1–L5A (D800–0024). 

(3) You may review copies of the service 

information incorporated by reference 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on August 

25, 2008. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–20494 Filed 9–8–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0955; Directorate 

Identifier 2008–CE–040–AD; Amendment 

39–15668; AD 2008–19–01] 

RIN 2120–AA64 

Airworthiness Directives; Harco Labs, 

Inc. Pitot/AOA Probes (Part Numbers 

100435–39, 100435–39–001, 100435–40, 

and 100435–40–001) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Harco Labs, Inc. part numbers 100435–

39, 100435–39–001, 100435–40, and 

100435–40–001 pitot/angle of attack 

(AOA) probes installed on, but not 

limited to Eclipse Aviation Inc. Model 

EA500 airplanes. This AD requires you 

to incorporate information into the 

Limitations section of the airplane flight 

manual (AFM) that will allow operation 

only under day visual flight rules (VFR) 

and allow only a VFR flight plan. This 

AD also requires you to test the pitot/ 

AOA probes for heater performance and 

replace the pitot/AOA probe if it fails 

the heater performance test. This AD 

results from several reports of airspeed 

disagree caution indication due to 

blockage from freezing condensation 

within the pitot/AOA system. We are 

issuing this AD to detect and correct 

improperly performing pitot/AOA probe 

heaters, which could result in blockage 

within the pitot/AOA system from 

condensation freezing with consequent 

incorrect indication of impact air 

pressure (airspeed/AOA). This blockage 

could lead to the stall warning 

becoming unreliable and the stick 

pusher, overspeed warning, autopilot, 

and yaw damper to malfunction. 

DATES: This AD becomes effective on 

September 29, 2008. 

On September 29, 2008, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

We must receive any comments on 

this AD by November 10, 2008. 

ADDRESSES: Use one of the following 

addresses to comment on this AD. 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M–

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M–

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

To get the service information 

identified in this AD, contact Harco 

Labs, Inc. 186 Cedar Street, Branford, 

Connecticut 06405; telephone: (203) 

483–3700; fax: (203) 483–3701, and 

Eclipse Aviation, 2503 Clark Carr Loop 

SE, Albuquerque, New Mexico 87106; 

telephone: (505) 245–7555; fax: (505) 

241–8802. 

To view the comments to this AD, go 

to http://www.regulations.gov. The 

docket number is FAA–2008–0955; 

Directorate Identifier 2008–CE–040–AD. 

FOR FURTHER INFORMATION CONTACT: 

Solomon Hecht, Aerospace Engineer, 12 

New England Executive Park, 

Burlington, Massachusetts 01803; 

telephone: (781) 238–7159; fax: (781) 

238–7170. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received several reports of 

airspeed disagree caution indication due 

to blockage within the pitot/AOA 

system from freezing condensation. We 

are issuing this AD to detect and correct 

improperly performing pitot/AOA probe 

heaters. 

This condition, if not corrected, could 

result in a blockage within the pitot/ 

AOA system from condensation freezing 

with consequent incorrect indication of 

impact air pressure (airspeed/AOA). 

This blockage could lead to the stall 

warning becoming unreliable and the 

stick pusher, overspeed warning, 

autopilot, and yaw damper to 

malfunction. 

Relevant Service Information 

We reviewed Harco Labs, Inc. Service 

Bulletin SB–34–10–10–001, Revision F, 

dated August 19, 2008; Harco Pitot AOA 

Probe Internal Tubing Heater 

Verification Test Procedure No. P1149, 

Rev: E, referenced in 8. Appendix A of 

Harco Labs, Inc. Service Bulletin SB–


yshivers on PROD1PC62 with RULES