Federal Register / Vol. 66, No. 88 / Monday, May 7, 2001 / Rules and Regulations 22913

Modification

(f) For airplanes having line numbers 153,

339, 416, and 540: Prior to the accumulation

of 60,000 total flight cycles, or within 3,000

flight cycles after the effective date of this

AD, whichever occurs later, modify the

fuselage circumferential skin joints in

accordance with Part IV of the

Accomplishment Instructions of Boeing

Service Bulletin 727–53–0084, Revision 4,

dated August 2, 1990. Such action constitutes

terminating action for the requirements of

paragraph (c)(2) of this AD.

Alternative Methods of Compliance

(g)(1) 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, Seattle

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Seattle ACO.

(2) An alternative method of compliance

for paragraph (f) of this AD that provides an

acceptable level of safety may be used in

accordance with data meeting the type

certification basis of the airplane approved

by a Boeing Company DER who has been

authorized by the Manager, Seattle ACO, to

make such findings.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permits

(h) 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 airplane to a

location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(i) Except as provided by paragraph (e) of

this AD, the actions shall be done in

accordance with Boeing Service Bulletin

727–53–0084, Revision 4, dated August 2,

1990. 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 Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington 98124–

2207. Copies may be inspected 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.

(j) This amendment becomes effective on

June 11, 2001.

Issued in Renton, Washington, on April 26,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–10939 Filed 5–4–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–SW–27–AD; Amendment

39–12217; AD 2001–09–11]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron, Inc. Model 412

Helicopters and Agusta S.p.A. Model

AB412 Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD)

that applies to certain serial-numbered

Bell Helicopter Textron, Inc. (Bell)

Model 412 helicopters and Agusta

S.p.A. (Agusta) Model AB412

helicopters. That AD currently requires

a temporary reduction of the neverexceed velocity (Vne) limitation until an

inspection of the tail rotor yoke (yoke)

assembly for fatigue damage and

installation of a redesigned yoke

flapping stop are accomplished.

Recurring periodic and special

inspections to detect occurrences of

yoke overload are also required. This

amendment requires the same actions as

the previous AD but expands the

applicability of the AD to all Bell Model

412, 412CF, 412EP, and Agusta Model

AB412 helicopters. This amendment is

prompted by the determination that the

unsafe condition exists on all Bell

Model 412 and all Agusta Model AB412

helicopters, regardless of serial number.

The actions specified by this AD are

intended to prevent static and dynamic

overload damage to the yoke that could

result in loss of the tail rotor and

subsequent loss of control of the

helicopter.

DATES: Effective June 11, 2001.

The incorporation by reference of

certain publications listed in the

regulations was approved previously by

the Director of the Federal Register as of

April 8, 1998 (63 FR 14026, March 24,

1998), as corrected on July 20, 1998 (63

FR 38742).

ADDRESSES: The service information

referenced in this AD may be obtained

from Bell Helicopter Textron, Inc., P.O.

Box 482, Fort Worth, Texas 76101,

telephone (817) 280–3391, fax (817)

280–6466 for the Bell Model 412

helicopters; and Agusta S.p.A., 21017

Cascina Costa di Samarate (VA), Italy,

Via Giovanni Agusta 520, telephone 39

(0331) 229111, fax 39 (0331) 229605–

222595 for the Agusta Model AB412

helicopters. 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:

Uday Garadi, Aviation Safety Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Standards Staff, 2601 Meacham Blvd.,

Fort Worth, Texas 76137, telephone

(817) 222–5123, fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 98–07–03,

Amendment 39–10421 (63 FR 14026,

March 24, 1998), which applies to

certain serial-numbered Bell Model 412

helicopters and Agusta Model AB412

helicopters, was published in the

Federal Register on January 22, 2001

(66 FR 6494). That action proposed to

require a reduction of the Vne limitation

until an inspection of the yoke assembly

for static and dynamic overload damage

and installation of a redesigned yoke

flapping stop are accomplished and

includes periodic and special

inspections to detect a yoke overload. A

correction to a technical bulletin date

referenced in that AD was issued on

July 10, 1998 (63 FR 38742, July 20,

1998).

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

clarifying changes that were made in

paragraph (a) to better explain the intent

of the AD and editorial changes in

paragraph (d). 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 135

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 6.5 work hours per

helicopter to install the placard, inspect

the yoke assembly, and install the yoke.

Required parts will cost approximately

$511 per helicopter. Based on these

figures, the total cost impact of this AD

on U.S. operators is estimated to be

$121,635.

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

22914 Federal Register / Vol. 66, No. 88 / Monday, May 7, 2001 / Rules and Regulations

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 39–10421 (63 FR

14026, March 24, 1998, and 63 FR

38742, July 20, 1998), and by adding a

new airworthiness directive (AD),

Amendment 39–12217, to read as

follows:

2001–09–11 Bell Helicopter Textron, Inc.

and Agusta S.p.A.: Amendment 39–

12217. Docket No. 99–SW–27–AD.

Supersedes AD 98–07–03, Amendment

39–10421, Docket No. 97–SW–58–AD.

Applicability: Bell Helicopter Textron, Inc.

Model 412, 412CF, and 412EP helicopters

and Agusta S.p.A. Model AB412 helicopters,

with tail rotor yoke assembly, part number

(P/N) 212–011–702-all dash numbers,

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 prevent static and dynamic overload

damage to the tail rotor yoke (yoke) that

could result in loss of the tail rotor and

subsequent loss of control of the helicopter,

accomplish the following:

(a) Before further flight, review the

historical records of the yoke assembly for

any static or dynamic overload damage that

could have imposed a bending load on the

yoke. The damage may not have required

replacing the yoke assembly; for example, an

incident in which a damaged tail rotor blade

was replaced due to a blade strike. If the

records indicate that overload damage may

have occurred, replace the yoke with an

airworthy yoke.

(b) Before further flight, unless the

requirements of paragraph (c) of this AD have

been accomplished previously:

(1) Install a Never Exceed Velocity (Vne)

red line at 120 knots indicated airspeed

(KIAS) on the pilot and copilot airspeed

indicators using red tape or paint and a

slippage indicator on the instrument case and

glass.

(2) Install a placard made of material that

is not easily erased, disfigured, or obscured

on the instrument panel in clear view of the

pilot and copilot:

‘‘Observe temporary Maximum Never

Exceed (Vne) airspeed red line (marked at

120 knots indicated airspeed (KIAS)). Vne is

20 KIAS less than the value presented on the

airspeed limitation placard for each ambient

condition.’’

(3) Insert the applicable Bell Helicopter

Textron (BHT) 412 Temporary Revision,

dated August 16, 1996, into the Model 412

Rotorcraft Flight Manual (RFM) or the

applicable section of Agusta AB412

Temporary Revision No. 2, dated April 17,

1997, into the Model AB412 RFM.

(c) Within 180 calendar days:

(1) Remove yoke assembly, P/N 212–011–

702-all dash numbers, and replace it with an

airworthy yoke assembly, P/N 212–011–702-

all dash numbers, with zero hours time-inservice (TIS), or an airworthy yoke

(regardless of TIS) that has passed a one-time

x-ray diffraction inspection in accordance

with BHT Alert Service Bulletin (ASB) 412–

96–89, Revision A, dated October 17, 1997;

BHT ASB 412CF–96–01, dated September 3,

1996; or Agusta Bolletino Tecnico (Technical

Bulletin) No. 412–65, dated April 17, 1997,

whichever is applicable.

(2) Install an airworthy tail rotor flapping

stop, P/N 212–011–713–103.

(3) After the requirements of paragraphs

(c)(1) and (c)(2) of this AD are accomplished,

remove the 120 KIAS redline from the pilot

and copilot airspeed indicators; remove the

Vne airspeed restriction placard; and remove

the BHT 412 Temporary Revision, dated

August 16, 1996; BHT ASB 412CF–96–01,

dated September 3, 1996; or Agusta AB412

Temporary Revision No. 2, as applicable,

from the RFM.

(d) After accomplishing the requirements

of paragraph (c) of this AD, at intervals not

to exceed 25 hours TIS, inspect the yoke

assembly and tail rotor flapping stop (stop)

in accordance with Part III, Recurring 25-

Hour Special Inspection and Conditional

Inspection Requirement, of BHT ASB 412–

96–89, Revision A, dated October 17, 1997;

BHT ASB 412CF–96–01, dated September 3,

1996; or Agusta Technical Bulletin No. 412–

65, dated April 17, 1997, as applicable.

Replace any unairworthy yoke assembly or

stop with an airworthy yoke assembly or stop

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, Regulations

Group, Rotorcraft Directorate, FAA.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Regulations Group.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Regulations Group.

(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 at

airspeeds not to exceed 120 KIAS to a

location where the requirements of this AD

can be accomplished.

(g) The inspections and installations shall

be done in accordance with Bell Helicopter

Textron Alert Service Bulletin 412–96–89,

Revision A, dated October 17, 1997; Bell

Helicopter Textron Alert Service Bulletin

412CF–96–01, dated September 3, 1996; or

Agusta Bolletino Tecnico (Technical

Bulletin) No. 412–65, dated April 17, 1997.

The incorporation by reference of those

documents was approved previously by the

Director of the Federal Register, in

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

part 51, as of April 8, 1998 (63 FR 14026,

March 24, 1998), as corrected on July 20,

1998 (63 FR 38742). Copies may be obtained

from Bell Helicopter Textron, Inc., P.O. Box

482, Fort Worth, Texas 76101, telephone

(817) 280–3391, fax (817) 280–6466; or

Agusta, 21017 Cascina Costa di Samarate

(VA), Via Giovanni Agusta 520, telephone

(0331) 229111, fax (0331) 229605–222595.

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

June 11, 2001.

Note 3: The subject of this AD is addressed

in Registro Aeronautico Italiano (Italy) AD

97–223, dated August 1, 1997.

Issued in Fort Worth, Texas, on April 20,

2001.

Larry M. Kelly,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 01–10731 Filed 5–4–01; 8:45 am]

BILLING CODE 4910–13–U