Federal Register / Vol. 66, No. 87 / Friday, May 4, 2001 / Rules and Regulations 22431

to perform critical functions are not

adversely affected when the airplane is

exposed to high intensity radiated

fields.

2. For the purpose of these special

conditions, the following definition

applies:

Critical Functions: Functions whose

failure would contribute to or cause a

failure condition that would prevent the

continued safe flight and landing of the

airplane.

Issued in Renton, Washington, on April 17,

2001.

Ali Bahrami,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–11253 Filed 5–3–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–40–AD; Amendment

39–12216; AD 94–14–20 R1]

RIN 2120–AA64

Airworthiness Directives; Sikorsky

Aircraft Corporation Model S–76A

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment revises an

existing airworthiness directive (AD) for

Sikorsky Aircraft Corporation (Sikorsky)

Model S–76A helicopters. That AD

currently requires a one-time inspection

of the tail rotor blade (blade) spar

elliptical centering plug (centering plug)

for disbonding and the addition of a

retaining pad on the pitch change shaft

between the output tail rotor gearbox

flange and the inboard tail rotor spar.

This amendment contains the same

requirements as the existing AD but

clarifies that the 500-hour time-inservice (TIS) repetitive inspections,

which could cause inadvertent damage,

are not required. This AD also

incorporates by reference a revised alert

service bulletin (ASB) that does not

include the 500-hour TIS repetitive

inspections. This amendment is

prompted by operator confusion about

whether the current AD continues to

require the 500-hour TIS repetitive

inspections. The actions specified by

this AD are intended to verify that the

FAA has determined that the 500-hour

TIS repetitive inspections are not

required to prevent the centering plug

from disbonding and moving out of

position, loss of tail rotor control, and

subsequent loss of control of the

helicopter.

DATES: Effective June 8, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 8,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Sikorsky Aircraft Corporation,

Attn: Manager, Commercial Tech

Support, 6900 Main Street, Stratford,

Connecticut 06614, phone (203) 386–

3001, fax (203) 386–5983. This 1

information may be examined at the

FAA, Office of the Regional Counsel,

Southwest Region, 2601 Meacham

Blvd., Room 663, Fort Worth, Texas; or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Richard Noll, Aviation Safety Engineer,

Boston Aircraft Certification Office, 12

New England Executive Park,

Burlington, MA 01803, telephone (781)

238–7160, fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by revising AD 94–14–20, Amendment

39–8969 (59 FR 41238, August 11,

1994), which applies to Sikorsky Model

S–76A helicopters, was published in the

Federal Register on January 30, 2001

(66 FR 8184). The action proposed to

require a one-time inspection of the

blade centering plug for disbonding and

the addition of a retaining pad on the

pitch change shaft between the output

tail rotor gearbox flange and the inboard

tail rotor spar. The action also clarified

that 500-hour TIS repetitive inspections,

which could cause inadvertent damage,

are not required and proposed to

incorporate by reference a revised ASB

that does not include the 500-hour TIS

repetitive inspections.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed except for some

editorial changes that are made in

paragraphs (a) and (e). These changes

were made to better identify the service

information that is incorporated by

reference. The FAA has determined that

these changes will neither increase the

economic burden on any operator nor

increase the scope of the AD.

The FAA estimates that this AD will

affect 150 helicopters of U.S. registry.

This revised AD will not impose any

additional burden or costs.

The regulations adopted herein 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. Therefore, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

For the reasons discussed above, I

certify that this action (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. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (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. Section 39.13 is amended by

removing Amendment 39–8969 (59 FR

41238, August 11, 1994), and by adding

a new airworthiness directive (AD),

Amendment 39–12216, to read as

follows:

94–14–20 R1 Sikorsky Aircraft

Corporation: Amendment 39–12216.

Docket No. 2000–SW–40–AD. Revises

AD 94–14–20, Amendment 39–8969,

Docket No. 93–SW–13–AD.

Applicability: Model S–76A helicopters,

with tail rotor blade (blade) assembly, part

number (P/N) 76101–05001 (all dash

numbers) or 76101–05101 (all dash

numbers), installed with more than 130

22432 Federal Register / Vol. 66, No. 87 / Friday, May 4, 2001 / Rules and Regulations

hours time-in-service (TIS), certificated in

any category.

Note 1: This AD applies to each helicopter

identified in the preceding applicability

provision, regardless of whether it has been

otherwise modified, altered, or repaired in

the area subject to the requirements of this

AD. For helicopters that have been modified,

altered, or repaired so that the performance

of the requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (c) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required within 25 hours TIS,

unless accomplished previously.

To prevent the blade spar elliptical

centering plug (centering plug) from

disbonding and moving out of position, loss

of tail rotor control, and subsequent loss of

control of the helicopter, accomplish the

following:

(a) Inspect the centering plug for

disbonding of the polyurethane filler that

fills the space between the aluminum

centering plug and the graphite spar in

accordance with the Accomplishment

Instructions, paragraph 3.A.(1) and (2), of

Sikorsky Aircraft Corporation Alert Service

Bulletin No. 76–65–35B (153B), Revision B,

dated October 2, 1997 (ASB).

Note 2: The 500-hours TIS repetitive

inspections contained in the

Accomplishment Instructions, paragraph

3.D., of Sikorsky Aircraft Corporation Alert

Service Bulletin 76–65–35A, Revision A,

dated February 29, 1984, are not required by

this AD.

(1) If the inspection of the centering plug

reveals disbonding of 1⁄2-inch or less in

length, install a retaining pad, P/N 76102–

05004–111, in accordance with the

Accomplishment Instructions, paragraph

3.C., of the ASB.

(2) For disbonds greater than 1⁄2-inch in

length, repair the blade assembly in

accordance with the Accomplishment

Instructions, paragraph 3.B.(1), of the ASB

except you are not required to contact

Sikorsky Worldwide Customer Service. If

blades are found with polyurethane filler

excessively cracked or deteriorated to extent

of breaking away from the spar or aluminum

plug by 0.005-inch or greater, replace the

blade with an airworthy blade.

(3) For spars with complete spar to

centering plug disbond in which the

polyurethane filler is intact and remains fully

bonded to the centering plug, repair the blade

assembly in accordance with the

Accomplishment Instructions, paragraph

3.B.(2), of the ASB.

(4) For spars with complete polyurethane

filler to centering plug disbond in which the

polyurethane filler is intact and remains fully

bonded to the spar, repair the blade assembly

in accordance with the Accomplishment

Instructions, paragraph 3.B.(3) of the ASB.

(b) Install a retaining pad, P/N 76102–

05004–111, in accordance with the

Accomplishment Instructions, paragraph

3.C., of the ASB.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Boston

Aircraft Certification Office, FAA. Operators

shall submit their requests through an FAA

Principal Maintenance Inspector, who may

concur or comment and then send it to the

Manager, Boston Aircraft Certification Office.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Boston Aircraft

Certification Office.

(d) Special flight permits may be issued in

accordance with 14 CFR 21.197 and 21.199

to operate the helicopter to a location where

the requirements of this AD can be

accomplished if a retaining pad has been

installed.

(e) The inspections, modifications, and

repair shall be done in accordance with the

Accomplishment Instructions, paragraphs

3.A.(1), 3.A.(2), 3.B.(1), 3.B.(2), 3.B.(3), and

3.C., of Sikorsky Aircraft Corporation Alert

Service Bulletin No. 76–65–35B (153B),

Revision B, dated October 2, 1997. This

incorporation by reference was approved by

the Director of the Federal Register in

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

part 51. Copies may be obtained from

Sikorsky Aircraft Corporation, Attn: Manager,

Commercial Tech Support, 6900 Main Street,

Stratford, Connecticut 06614, phone (203)

386–3001, fax (203) 386–5983. Copies may be

inspected at the FAA, Office of the Regional

Counsel, Southwest Region, 2601 Meacham

Blvd., Room 663, Fort Worth, Texas; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment becomes effective on

June 8, 2001.

Issued in Fort Worth, Texas, on April 20,

2001.

Larry M. Kelly,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 01–10730 Filed 5–3–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–352–AD; Amendment

39–12214; AD 2001–09–09]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A330 and A340 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A330 and A340 series airplanes. This

action requires a one-time inspection to

verify the proper configuration of the

drive assemblies for the low-pressure

and, for certain airplanes, the cross-feed

fuel valves; and corrective action, if

necessary. This action is necessary to

prevent failure of the low-pressure and/

or cross-feed fuel valves, which could

result in the inability to shut off the fuel

supply to the engine and exacerbate an

engine fire, or the inability to cross-feed

fuel when required. This action is

intended to address the identified

unsafe condition.

DATES: Effective May 21, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 21,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

June 4, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket 2000–NM–352–

AD, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056. Comments

may be inspected at this location

between 9:00 a.m. and 3:00 p.m.,

Monday through Friday, except Federal

holidays. Comments may be submitted

via fax to (425) 227–1232. Comments

may also be sent via the Internet using

the following address: 9-anmiarcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2000–NM–352–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

The service information referenced in

this AD may be obtained from Airbus

Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Todd Thompson, Aerospace Engineer,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–1175;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: The

Direction Generale de l’Aviation Civile

(DGAC), which is the airworthiness

authority for France, notified the FAA