49132 Federal Register / Vol. 62, No. 182 / Friday, September 19, 1997 / Rules and Regulations

PART 316—GENERAL

REQUIREMENTS FOR

NATURALIZATION

1. The authority citation for part 316

continues to read as follows:

Authority. 8 U.S.C. 1103, 1181, 1182, 1443,

1447; 8 CFR 2.

§ 316.20 [Amended]

2. In § 316.20, paragraph (a) is

amended by adding the American

institution of research ‘‘Missouri

Botanical Garden (research and

educational programs only)’’

immediately after ‘‘Michigan State

University, East Lansing, MI.’’

Dated: September 5, 1997.

Doris Meissner,

Commissioner, Immigration and

Naturalization Service.

[FR Doc. 97–24912 Filed 9–18–97; 8:45 am]

BILLING CODE 4410–10–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–SW–18–AD; Amendment

39–10026; AD 97–19–06]

RIN 2120–AA64

Airworthiness Directives; Sikorsky

Aircraft Corporation Model S–61A, D,

E, L, N, NM, R, and V Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

an existing priority letter airworthiness

directive (AD), applicable to Sikorsky

Aircraft Corporation Model S–61A, D, E,

L, N, NM, R, and V helicopters, that

currently requires inspecting certain

main rotor blade assemblies (blades) to

determine if a blade has a blade trailing

edge pocket assembly (pocket assembly)

that was anodized by Poly-Metal

Company during a specified time

period, and if so, replacing it with an

airworthy blade. This amendment

requires the same actions as the existing

AD, but corrects two serial numbers in

the list of the applicable blades. This

amendment is prompted by the

manufacturer’s issuance of a service

bulletin with a revised list of blade

serial numbers. The actions specified by

this AD are intended to prevent

disbonding and separation of portions of

the blade, subsequent excessive

vibrations, and loss of control of the

helicopter.

DATES: Effective October 6, 1997. The

incorporation by reference of certain

publications listed in the regulations is

approved by the Director of the Federal

Register as of October 6, 1997.

Comments for inclusion in the Rules

Docket must be received on or before

November 18, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 97–SW–18–AD, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas 76137.

The service information referenced in

this AD may be obtained from Sikorsky

Aircraft Corporation, Attn: Mr. Paul

Dionne, CAR Office, 6900 Main Street,

P.O. Box 9729, Stratford, Connecticut

06497–9129, telephone (203) 386–7860,

fax (203) 386–4703. This information

may be examined at the FAA, Office of

the Assistant Chief Counsel, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas 76137; or at the Office of the

Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT: Mr.

Bob Mann, Aerospace Engineer, Boston

Aircraft Certification Office, ANE–150,

12 New England Executive Park,

Burlington, MA 01803, telephone (617)

238–7190, fax (617) 238–7199.

SUPPLEMENTARY INFORMATION: On April

30, 1997, the FAA issued priority letter

AD 97–10–04 to require, before further

flight, inspecting certain blades to

determine the anodizing date for certain

pocket assemblies installed on the

blade, and if a blade has a pocket

assembly that was anodized by PolyMetal Company from October 1, 1996

through December 31, 1996, replacing it

with an airworthy blade. That action

was prompted by the discovery of a

manufacturing defect that may cause

disbonding and separation of portions of

a blade. This defect is the result of an

anodizing process, used during the

manufacture of the pocket assembly,

that did not meet the Type Design

specifications. That condition, if not

corrected, could result in disbonding

and separation of portions of the blade,

subsequent excessive vibrations, and

loss of control of the helicopter.

Since the issuance of that AD,

Sikorsky Aircraft Corporation has issued

Sikorsky Alert Service Bulletin (ASB)

No. 61B15–29A, Revision A, dated May

9, 1997, which corrects two of the blade

serial numbers listed in the ASB that

were referenced in the priority letter

AD.

Since an unsafe condition has been

identified that is likely to exist or

develop on other Sikorsky Aircraft

Corporation Model S–61A, D, E, L, N,

NM, R, and V helicopters of the same

type design, this AD supersedes AD 97–

10–04 to require, before further flight,

inspecting certain blades to determine

the anodizing date for certain pocket

assemblies installed on the blade, and if

a blade has a pocket assembly that was

anodized by Poly-Metal Company

during the period of October 1, 1996,

through December 31, 1996, replacing it

with an airworthy blade. The actions are

required to be accomplished in

accordance with the service bulletin

described previously.

Since a situation exists that requires

the immediate adoption of this

regulation, it is found 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

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this rule by

submitting such written data, views, or

arguments as they may desire.

Communications should identify the

Rules Docket number and be submitted

in triplicate to the address specified

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 97–SW–18–AD.’’ The

postcard will be date stamped and

returned to the commenter.
Federal Register / Vol. 62, No. 182 / Friday, September 19, 1997 / Rules and Regulations 49133

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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

adding a new airworthiness directive

(AD), Amendment 39–10026, to read as

follows:

97–19–06 Sikorsky Aircraft Corporation:

Amendment 39–10026. Docket No. 97–

SW–18–AD. Supersedes priority letter

AD 97–10–04.

Applicability: Model S–61A, D, E, L, N,

NM, R, and V helicopters, certificated in any

category, with a main rotor blade assembly

(blade), part number (P/N) S6115–20501 or

P/N 61170–20201, installed, having one of

the following four-digit or eight-digit serial

numbers:

1282–1554 3305–3106

2183 3317–3115

2380–2498 3343–3147

2495 3343–3648

2500 3364–3180

2520 3451–3239

2521 3491–3278

2644 3499–3936

2673 3511–3293

2716–2683 3512–3292

2721 3517–3311

2751 3525–3310

2781–2644 3637–3459

2800–2671 3694–3481

2817 3748–3543

2819 3752–3527

2839 3753–3528

2883 3840–3620

2919–2771 3966–3737

3008 4216–4392

3016–2850 4787–4793

3019 4800–4794

3138 4835–4790

3168–3585 5484–5363

3192–2999 5974–5816

3215–3012 5981–5813

3216–3023 7069–6583

3242–3044 7779–7033

3249–3052 8099–8054

3250–3043

Note 1: This AD applies to each helicopter

identified in the preceding applicability

provision, regardless of whether it has been

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 use the authority

provided in paragraph (b) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any helicopter

from the applicability of this AD.

Compliance: Required before further flight,

unless accomplished previously.

To prevent disbonding and separation of

portions of the blade, subsequent excessive

vibrations, and loss of control of the

helicopter, accomplish the following:

(a) Inspect each blade having one of the

affected serial numbers in accordance with

Section 2A of the Accomplishment

Instructions of Sikorsky Alert Service

Bulletin (ASB) No. 61B15–29A, Revision A,

dated May 9, 1997, to determine the

anodizing date for all blade trailing edge

pocket assemblies (pocket assemblies)

installed on the blade in locations as

specified in the Planning Information

Section, paragraph 1D(3) of the ASB, that

were anodized by Poly-Metal Company.

Remove any blade having a pocket assembly

anodized by Poly-Metal Company during the

period from October 1, 1996 through

December 31, 1996, and replace the blade

with an airworthy blade.

(b) 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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Boston Aircraft

Certification Office.

(c) A one-time only special flight permit

may be issued to operate the helicopter to a

location where the requirements of this AD

can be accomplished, after inspecting all

pocket assemblies for disbonding.

(d) The inspection shall be done in

accordance with Sikorsky ASB No. 61B15–

29A, Revision A, dated May 9, 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: Mr. Paul

Dionne, CAR Office, 6900 Main Street, P.O.

Box 9729, Stratford, Connecticut 06497–

9129, telephone (203) 386–7860, fax (203)

386–4703. Copies may be inspected at the

FAA, Office of the Assistant Chief Counsel,

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.

(e) This amendment becomes effective on

October 6, 1997.

Issued in Fort Worth, Texas, on September

3, 1997.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–24075 Filed 9–18–97; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–ANE–32; Amendment 39–

10133; AD 97–19–12]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney JT8D Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Pratt & Whitney JT8D–1,

–1A, –1B, –7, –7A, –7B, –9, –9A, –11,

–15, –17, and –17R series turbofan

engines, that requires initial and

repetitive fluorescent penetrant and

eddy current inspections of 4th stage

low pressure turbine (LPT) hubs for

cracks, and, if necessary, replacement

with serviceable parts. This amendment