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-AF:l13. dated February 22. 2007 section

3 AC1;OmplishmentInstructions. Engines on

which cracldng is found should be rejected

from service.

Inspection-In-Shop

(2) Applicable to RRTrent 500, 700 llnd

800 engines at each shop visit in which the

engine is sufficiently disassembled to access

the !P Compressor Module rear face: Inspect

ilie lP Compressor rolor rear balance land for

cracks in accordance with Rolls-Royce R.B211

Propulsion System Alert Non Modification

Service Bulletin RB.211-7Z-AF260, Revision

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

3 Accomplishment Instructions.

Other FAA AD Provisions

If] 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 CPR 39.19.

Related Information

(g)Refer to EASA Airworthiness Direcliva

2007-0052, dated February 23, 2007, for

related information.

(h) Contact James Lawrence. Aerospace

Engineer. Engine Certification Office, FAA.

Engine and Propeller DiredoraLe, 12 New

England Executive Park. Burlington, MA

01803; e·mail: jomes.1owrenee@/rJrl.gov;

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

7199, for more information about this AD.

Material Incorporated by Reference

IiI 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 th8 Federol Register

approved the incorporation by reference of

this service infonnation under 5 U.S_C.

552(a) and 1 CFR pert 51.

(2) For service inIormation identified in

this AD, contaCl Rolls-Royce pic, P.O. Box

31, Derby. DE24 BBJ.United Kingdom:

telephone: 44 (0)1332-242424; fax: 44 {OJ

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 infonnation on

the availability of this material at NAKA, call

(202) 741-6030, or go to: http://

www.archives.govlfederoJ-regi!ilerlcjr/jbr.

locations.htm/.

TABLE 1-MATERIAL iNCORPORATED BY REFERENCE

Alert Service Bulletin No. Page Revision Date

RB.211-72-AF260; TOlal pages-11 ALL

RB.211-72-AF260; Tota! pages-11 ._...... ALL

RB.211-72-AF260; Total pages~11 .. All

RB.211-72-AF313; Total pages-11 ALL

··::·:::.::·::::::::::.::::i···········

•.•.••..•..••.• I ••••.••••

················::::-:T·········

Original October 17, 2006.

1 January 17. 2007.

2 _.. July 4, 2007.

Original.,... February 22, 2007.

Issued in Burlington, Massachusetts. on

Augusl 25, 2008.

Mark A. Rumizen,

ActingMonuger, Engineund Propeller

Directorate, Aircroft Certifieulion SelVioo.

[FR Doc. E3-20212 Filed 9-8-08; 8:45 ami

ellllNG COOE491G-l:J-f'

DEPARTMENT OF TRANSPORT AnON

Federal Aviation Administration

14 CFR Part 39

{Docket No. FAA-2ooe-0946; DIrectorate

Identifier 200e-NM-147-AD; Amendment

39-15667; AD 2008-18-10]

RIN212Q-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-9()-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

I

delect 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. I

ADDRESSES:You may send comments by

any of the following method$':

• Federal eRulema1dng Porlal: Go to

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

instructions for submitting comments.

• Fax: 202-493-2251.

• Mail: U.S. Department of

Transportation, Docket Operations. M30, West Building Ground Floor, Room

WI2-140, 1200 New Jersey Avenue, SE.,

Washington, DC 20590.

• Hand Delivery: U.S. Department of

Transportation, Docket Operations, M30, West Building Ground Floor, Room

W12-140, 1200 New Jersey Jj\venue, SE .•

Washington, DC 20590, bet;'Yeen 9 a.m.

and 5 p.m., Monday througH Friday,

except Federal holidays. I

For service information identified in

this AD, contact Boeing Corrtmercial

Airplanes, Long Beach Divis:ion, 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://

Ivv.w.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 80Q-647-

5527) is in the ADORESSESsection.

Comments will be available in the AD

docket shortly after receipt.

FORFURTHERINFORMATIONCONTACT:

Roger Durbin, Aerospace Engineer,

Airframe Branch, ANM-120L, FAA, Los

Angeles Aircraft Certification Office,

3950 Paramount Boulevard, Lakewood,

California 90712-4137; telephone (562)

627-5233; fax {562l627-5210.

SUPPLEMENTARVINFORMATION:

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-9G--30 airplanes.

The airplanes had accumulated between

18,757 and 25,400 totai flight hours and

between 15,841 and Z7,OOOtotal flight

cycles. A safety assessment of the

missing fasteners has concluded that

loose or discrepant fasteners in the top
52204 Federal Register/Vol. 73, No. 175/Tuesday, September 9, 200s/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 COITected, could result in separation

of the engine from the airplane.

Relevant Service Information

We reviewed Boeing Alert Service

Bulletin MD9O--S4A002, dated August 1,

2008. The service bulletin describes

procedures for doing a detailed

inspection for certain defects of the

upper fasteners of the aft mounl 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 fasleners if any

defect is found.

FAA's Determination and Requirements

ofTbis 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 ofthe(se)

same type design(s). This AD requires

accomplishing the actions specified in

the service information described

previously.

Inlerim 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

he~on 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 YOue comments to an

address listed under the ADDRESSES

section. Include "Docket No. FAA2008-0946; Directorate Identifier 2008-

NM-147-AD" at the beginning of yo or

comments. We specifically invite

comments on the overall reg~latory,

economic, environmental, and energy

aspects of this AD. We will consider all

comments received by the closing date

and may amend this AD beca\Ise of

those comments.

We will post all comments we

receive, without change, to http://

www.regulotions.gov, including any

personal information you provide. We

will also post a report summarizing each

subslantive 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 VIT:

Aviation Programs," describes in more

detail the scope of the Agency's

authority.

We are issuing this rulema.king under

the authority described in "Subtitle VII,

Part A, Subpart Ill, Section 44701:

General requirements." Und~r that

section, Congress charges th~ FAA with

promoting safe flight of civillaiIcraft in

air commerce by prescribing regulations

for practices, methods, and procedures

the Administrator finds nec~ssary for

safety in air commerce. This1cegulation

is within the scope of that authority

because it addresses an unsafe condition

that is likely to exisl 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

Regulalory 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 oue 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-AlRWORTHlNESS

DIRECTIVES

• 1. The authority citation for part 39

continues to read as follows:

Authurity: '19 U.S.C. 106(g). 40113, 4,1701.

§39.13 (Amended}

.2. Tbe FAA amends §39.13 by adding

the following new AD:

2008-18....-10 M~Donnen Douglas:

Amendment 39-15667. Docket No.

FAA-2008-09<l6: Directorate Identifier

2008-NM-1<l7~AD.

Effective Date

(e)This airworthiness directive (AD) is

effective September 24. 2008_

Affected ADs

(bJ None.

Applicability

(e) This AD applies to McDonnell Dougles

Model MD-90-30 airplanas, o;<lrlificatlldin

any category; as identified in Boeing Alert

Service Bulletin MD9Q-54A002, dated

August 1. 2008.

Unsafe Condition

{d)This AD Nsulls from reports of loose,

cra~ked. or missing fasteners in the aft mount

support fitling of the left and right engines.

We are issuing this AD 10detect and correct

loose, cracked, or missing fasteners in the

engine aft support mount fitting, which could

lead to sepatation of Ihe support fitting from

the pylon, which could result in separation

of Ihe engine from the airplane.

Compliance

(el Comply with this AD within the

compliance times specified, unless already

done.

Detailed Inspection

(0 Within 703 flight cycles after the

effective dale of this AD, do a detailed
Federal Register/Vol. 73, No. 175/Tuesday, September g, ZOOS/Rulesand Regulations 52205

inspection for any derect Imissing, loose, or

damaged fasteners; incorrect gap between

washers and structure or between fastener

heads and structme; or incorrect torque of

fastener nuls) of the upper fasteners of the aft

mount support fitting of the left and right

engines, and do aU the applicable corrective

actions before further flight, by

accomplishing all of the applicable actions

specified in the Accomplishment

InstructiOns of Boeing Alert Service Bulletin

MD9G-54AOOZ,dated August I, 2008.

Credit for Actions Done per Multiple

Operator Message (MOM)

(g) Actions done before the effll(:tivedate

of this AU in accordance with Boeing MOM

1-89388Z781-2, dated July 25, zooa, are

acceptable for compliance with the

requirements of paragraph !Dof this AD.

Alternative Methods of Compliance

(AMOCs)

(h)(l) The Manager, Los Angeles

Certification Office (ACO), FAA, ATIN;

Roger Durbin, Aerospace Engineer, Airframa

Branch, ANM-120L, FAA. Los Angeles ACO,

3960 Paramount Boulevard, Lakewood,

California 90712-4137; telephone (562) 627-

5233; fax (56Z)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 (FSDOj, or lacking a PI, your local

FSOO.

(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 heen

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.

Materiallncorporatcd by Refereoce

(iJYou must use Boeing Alert SOfvice

Bulletin MD9Q-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 V.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; Darn and Service

Managemeot, Dept. CI-LSA (D80G-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; Drat

the National ArclJ.i"es and Records

Administration INARA). For information on

the availability of this material at NARA, call

202-741-60JO, Or go to: http://

Ivww.orchivcs.gov/federaCregis!er/

Cl}de_ofJedemLreguluUons/

ibclocuUolls.htmJ.

Issued in Renton. Washington, on August

25,2008.

Dionne Palermo,

Acting Monager, Trrmsport Airplane

Directorate. Aircraft Certifiection Service.

(FR Doc_E8--20494 Filed 9-8-08; 8:45 aml

61li.1HG CODE .!l1ll-'3-I'

DEPARTMENT OF TRANSPORTATION

Federal Aviation AdmInistration

14 CFR Part 39

(Docket No. FAA-2008-0955; Di~eclorate

Identifier 2008-CE-<l4Q-AD; Amendment

39-15668; AD 2008-19-01)

RIN212o-AA64

AirworthIness DIrectives; Harco Labs,

Inc. PitotfAOA 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.

SUMUARY:The FAA is adopting a new

airworthiness directive (AD) for certain

Hareo Labs. Inc. part numbers 100435-

39,100435-39-001,100435-40,and

100435-40-001 pitot/angle of attack

(ADA) probes installed on, but not

limited to Eclipse Aviation lnc. Model

EA50a 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 ~les (VFR)

and allow only a VFR flight plan. This

AD also requires you to test the pitotl

ADA probes for heater performance and

replace the pilot! ADA probelif it fails

the heater performance test This AD

results from several reports df airspeed

disagree caution indication due 10

blockage from freezing condensation

within the pitot! ADA system. We are

issuing this AD to detect and correct

improperly performing pitotl ADA probe

heaters, which could result in blockage

·within the pitot/ADA system from

condensation freezing with consequent

incorrect indication of impact air

pressure (airspeedl ADA). This blockage

could lead to the stall warning

becoming unreliable and the stick

pusher, overspeed warning, autopilot,

and yaw damper to malfunction.

OATES: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 conunent on this AD.

• Federal eRulemaking Portal: Go to

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

instructions for submitting comments.

• Fax: (202) 493-2251.

• Moil: U.S. Department of

Transportation, Docket Operations, M30, West Building Ground Floor, Room

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

Washington, DC 20590.

• Hand Delivery: U.S. Department of

Transportation, Docket Operations, M30, West Building Ground Floor, Room

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

Washington, DC 20590, between 9 a.m.

and 5 p.m., Monday..th'fOugh Friday,

except Federal 90fidays.

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-04G-AD.

FORFURTliERINFORMATIONCONTACT:

Solomon Hecbt. Aerospace Engineer, 12

New England Executive Park,

Burlington, Massachusetts 01803;

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

238-7170.

SUPPLEMENTARYINFORMATION:

Discussion

We received several reports of

airspeed disagree caution indication due

to blockage within the piloll AOA

system from freezing condensation. We

are issuing this AD to detect and correct

improperly perfonning pilot/ADA probe

heaters.

This condition, if not corrected, could

result in a blockage \vithin the pitot/

ADA system from condensation freezing

with consequent incorrect indication of

impact air pressure (airspeedJ ADA).

·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 Hareo Labs, Inc. Service

Bulletin SB-34-1O-1(}-QOl, Revision f,

dated August 19, 2008: Hareo Pitot ADA

Probe Internal Tubing Heater

Verification Test Procedure No. Pl149,

Rev; E, referenced in 8. Appendix A of

Harco Labs. Inc. Service Bulletin SB-