4654 Federal Register / Vol. 66, No. 12 / Thursday, January 18, 2001 / Rules and Regulations

Effective Date

(f) This amendment becomes effective on

February 22, 2001.

Issued in Renton, Washington, on January

8, 2001.

Dorenda D. Baker,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–1075 Filed 1–17–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–52–AD; Amendment

39–12074; AD 2001–01–04]

RIN 2120–AA64

Airworthiness Directives; Sikorsky

Aircraft Corporation Model S–76A, S–

76B, and S–76C Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) for

Sikorsky Aircraft Corporation (Sikorsky)

Model S–76A, S–76B, and S–76C

helicopters. This AD requires initial and

repetitive inspections of the main

landing gear positioning rod assembly

(rod assembly) and the side brace rod

end (rod end) for corrosion. If any

corrosion is found, this AD requires

replacing any part that is corroded with

an airworthy part before further flight.

This amendment is prompted by a

landing gear collapse caused by

corrosion due to dissimilar metals in the

landing gear rod end. The actions

specified in this AD are intended to

detect corrosion of the threaded joint in

the rod assembly to prevent a collapse

of the landing gear, and subsequent loss

of control of the helicopter during

landing.

DATES: Effective February 2, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February 2,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

March 19, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 2000–SW–

52–AD, 2601 Meacham Blvd., Room

663, Fort Worth, Texas 76137. You may

also send comments electronically to

the Rules Docket at the following

address: 9-asw-adcomments@faa.gov.

The service information referenced in

this AD may be obtained from BF

Goodrich Landing Gear Division, Attn.:

Kenneth R. Madej, 8000 Marble Ave.,

Cleveland, OH 44105, telephone (216)

429–4461, fax (216) 429–4357. This

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:

Jeffrey Lee, Aviation Safety Engineer,

Boston Aircraft Certification Office, 12

New England Executive Park,

Burlington, MA 01803, telephone (781)

238–7161, fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: This

amendment adopts a new AD for

Sikorsky Model S–76A, S–76B, and S–

76C helicopters. This AD requires,

within 14 days, inspecting the rod

assembly, part number (P/N) 1945E–

31A or 2071–31, and rod end, P/N

1945E235 or 2071–235, for corrosion. If

the rod assembly and rod end were

inspected and reassembled in

accordance with BF Goodrich

Component Maintenance Manual with

Illustrated Parts List, 1945/2071 Series

Main Landing Gear, No. 32–10–01,

(formerly titled Cleveland Pneumatic

Maintenance Manual 32–10–01),

Revision 4, dated December 15, 1994,

within the past 24 months, this AD

requires an inspection within 90 days.

If any corrosion is found, this AD

requires replacing the unairworthy part

with an airworthy part before further

flight. This AD also requires, at intervals

not to exceed 90 days, a repetitive

inspection for corrosion on certain rod

ends. For other rod ends, this AD

requires a repetitive inspection for

corrosion at intervals not to exceed 12

months or 1,500 hours time-in-service,

whichever occurs first. This AD is

prompted by a landing gear collapse on

a helicopter that was in a hangar.

Analysis showed that corrosion due to

dissimilar metals in the rod end caused

the rod end to fail with subsequent

collapse of the landing gear. The actions

specified in this AD are intended to

detect corrosion of the threaded joint in

the rod assembly and prevent a collapse

of the landing gear and subsequent loss

of control of the helicopter during

landing.

The FAA has reviewed BF Goodrich

Landing Gear Service Bulletin No. 76A–

32–03, Revision 1, dated September 15,

2000, which describes procedures for

inspecting and repairing or replacing

the rod end and rod assembly.

Since an unsafe condition has been

identified that is likely to exist or

develop on other Sikorsky Model S–

76A, S–76B, and S–76C helicopters of

the same type design, this AD is being

issued to detect corrosion of the

threaded joint in the rod assembly and

prevent a collapse of the landing gear.

This AD requires inspecting the rod

assembly and rod end for corrosion at

specified intervals and replacing, before

further flight, any component that has

corrosion. The actions must be

accomplished in accordance with the

service bulletin described previously.

The short compliance time involved is

required because the previously

described critical unsafe condition can

adversely affect the structural integrity

of the helicopter. Therefore, the actions

previously mentioned are required

within 14 days, and this AD must be

issued immediately.

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.

The FAA estimates that 180

helicopters will be affected by this AD

and that it will take approximately 4.5

work hours per helicopter to inspect the

rod assembly and rod end and 1.5 work

hours to remove and replace the rod

assembly and rod end, if necessary.

Required parts will cost approximately

$14,600 per helicopter. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$2,692,800 ($14,960 per helicopter,

assuming inspecting, removing, and

replacing the rod assembly and rod end

once).

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

Federal Register / Vol. 66, No. 12 / Thursday, January 18, 2001 / Rules and Regulations 4655

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 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 mailed

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. 2000–SW–

52–AD.’’ The postcard will be date

stamped and returned to the

commenter.

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.

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 to

read as follows:

2001–01–04 Sikorsky Aircraft Corporation:

Amendment 39–12074. Docket No. 2000–

SW–52–AD.

Applicability: Model S–76A, S–76B, and

S–76C helicopters up to and including serial

number 760513 with positioning rod

assembly (rod assembly), part number (P/N)

1945E–31A or 2071–31, or side brace rod end

(rod end), P/N 1945E–235 or 2071–235,

installed, 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 (e) 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 as indicated, unless

accomplished previously.

To detect corrosion of the threaded joint in

the rod assembly and prevent a collapse of

the landing gear and subsequent loss of

control of the helicopter during landing,

accomplish the following:

(a) Within 14 days, inspect the rod

assembly and rod end for corrosion in

accordance with Section 2., Accomplishment

Instructions, in BF Goodrich Service Bulletin

No. 76A–32–03, Revision 1, dated September

15, 2000 (SB), except that scrapping of

corroded parts is not required. Replace any

part that is corroded with an airworthy part

before further flight.

(b) Within 90 days, if the rod assembly and

rod end were inspected and reassembled in

accordance with BF Goodrich Component

Maintenance Manual with Illustrated Parts

List, 1945/2071 Series Main Landing Gear,

No. 32–10–01, (formerly titled Cleveland

Pneumatic Maintenance Manual 32–10–01),

Revision 4, dated December 15, 1994, within

the past 24 months, inspect the rod assembly

and rod end in accordance with Section 2. of

the SB. Scrapping of corroded parts is not

required. Replace any part that is corroded

with an airworthy part before further flight.

(c) At intervals not to exceed 90 days, for

rod ends that are not reassembled with

Mastinox sealant or reassembled with

Mastinox sealant but without cadmium plate

restoration, inspect the rod assembly and rod

end for corrosion in accordance with the

Section 2. of the SB, except that scrapping of

corroded parts is not required. Replace any

part that is corroded with an airworthy part

before further flight.

(d) At intervals not to exceed 12 months or

1,500 hours time-in-service, whichever

occurs first, for rod ends assembled with

Mastinox sealant and cadmium plate

restoration or for rod ends reassembled with

Mastinox but that did not previously require

rework due to corrosion, inspect the rod

assembly and rod end for corrosion in

accordance with the Section 2. of the SB,

except that scrapping of corroded parts is not

required. Replace any part that is corroded

with an airworthy part before further flight.

(e) 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 (ACO), 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 ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Boston ACO.

(f) Special flight permits may be issued in

accordance with §§ 21.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197

and 21.199) to operate the helicopter to a

location where the requirements of this AD

can be accomplished.

(g) The inspections shall be done in

accordance with Section 2., Accomplishment

Instructions, in BF Goodrich Service Bulletin

No. 76A–32–03, Revision 1, dated September

15, 2000. 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 BF Goodrich Landing Gear Division,

Attn.: Kenneth R. Madej, 8000 Marble Ave.,

Cleveland, OH 44105, telephone (216) 429–

4461, fax (216) 429–4357. 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.

(h) This amendment becomes effective on

February 2, 2001.

Issued in Fort Worth, Texas, on January 5,

2001.

Henry A. Armstrong,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 01–1121 Filed 1–17–01; 8:45 am]

BILLING CODE 4910–13–U