This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

62275

Vol. 65, No. 202

Wednesday, October 18, 2000

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–24–AD; Amendment

39–11930; AD 2000–20–18]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron Canada Model 407

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) for

Bell Helicopter Textron Canada (BHTC)

Model 407 helicopters. This AD requires

inspecting the brackets that attach each

horizontal stabilizer slat (slat) to the

stabilizer for a crack and replacing the

slat assembly if a crack is found.

Installing airworthy segmented slat

assemblies would be required prior to

flight after December 31, 2000 and

would constitute terminating action for

the requirements of this AD. This

amendment is prompted by an incident

in which a slat separated from a

helicopter. The actions specified by this

AD are intended to prevent a slat from

separating, impact with a main or tail

rotor blade, and subsequent loss of

control of the helicopter.

DATES: Effective November 22, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

22, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Bell Helicopter Textron Canada,

12,800 Rue de l’Avenir, Mirabel, Quebec

JON1LO, telephone (450) 437–2862 or

(800) 363–8023, fax (450) 433–0272.

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:

Sharon Miles, Aviation Safety Engineer,

FAA, Rotorcraft Directorate, Regulations

Group, Fort Worth, Texas 76193–0111,

telephone (817) 222–5122, fax (817)

222–5961.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

that applies to BHTC Model 407

helicopters was published in the

Federal Register on July 20, 2000 (65 FR

44994). That action proposed to require

visually inspecting certain brackets that

attach slots to the horizontal stabilizer

for a crack and replacing any slat

assembly that has a cracked bracket.

Also proposed was installing different

part-numbered airworthy segmented slat

assemblies on all affected models prior

to flight after December 31, 2000.

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.

The FAA estimates that 348

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 0.5 work hour per

helicopter to perform the visual

inspections, 1 work hour to replace a

slat assembly, and that the average labor

rate is $60 per work hour. Required

parts will cost approximately $2,364 per

segmented slat assembly. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$1,697,544, assuming 1 inspection per

helicopter and replacement of the 2 slat

assemblies on each helicopter.

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

adding a new airworthiness directive to

read as follows:

2000–20–18 Bell Helicopter Textron

Canada: Amendment 39–11930. Docket

No. 2000–SW–24–AD.

Applicability: Model 407 helicopters, serial

numbers 53000 through 53347, 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

62276 Federal Register / Vol. 65, No. 202 / Wednesday, October 18, 2000 / Rules and Regulations

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent a horizontal stabilizer slat (slat)

from separating, impact with a main or tail

rotor blade, and subsequent loss of control of

the helicopter, accomplish the following:

(a) Within 50 hours time-in-service (TIS)

and thereafter at intervals not to exceed 100

hours TIS, visually inspect the brackets, part

number (P/N) 206–023–119–109 or –110 or

P/N 407–023–801–127 or –128, that attach

the slats, P/N 407–023–002–117, to the

horizontal stabilizer for a crack.

(1) If any crack is found, replace the slat

assembly, P/N 407–023–002–117, with an

airworthy segmented slat assembly, P/N 407–

023–001–101, before further flight. Replace

the slat assembly in accordance with Part II

of the Accomplishment Instructions in Bell

Helicopter Textron Alert Service Bulletin No.

ASB 407–99–32, dated December 7, 1999.

(2) If no crack is found, replace each slat

assembly, P/N 407–023–002–117, with an

airworthy segmented slat assembly, P/N 407–

023–001–101, prior to flight after December

31, 2000.

(b) Installing airworthy segmented slat

assemblies, P/N 407–023–001–101,

constitutes terminating action for the

requirements of this AD.

(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, 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.

(d) Special flight permits may be issued in

accordance with sections 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.

(e) The modification shall be done in

accordance with Part II of the

Accomplishment Instructions in Bell

Helicopter Textron Alert Service Bulletin No.

ASB 407–99–32, dated December 7, 1999.

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 Bell Helicopter Textron Canada, 12,800

Rue de l’Avenir, Mirabel, Quebec JON1LO,

telephone (450) 437–2862 or (800) 363–8023,

fax (450) 433–0272. 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

November 22, 2000.

Note 3: The subject of this AD is addressed

in Transport Canada (Canada) AD CF–2000–

09, dated March 21, 2000.

Issued in Fort Worth, Texas, on September

29, 2000.

Henry A. Armstrong,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 00–26236 Filed 10–17–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–248–AD; Amendment

39–11932; AD 2000–20–20]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–400 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 747–

400 series airplanes, that requires

removal of existing inertial reference

units (IRU) and installation of modified

IRU’s. This amendment is prompted by

a report of the failure of the left and

center IRU’s on a single flight. The

actions specified by this AD are

intended to prevent loss of multiple

IRU’s in flight, which could result in the

loss of navigation data during flight.

This could compromise the ability of

the flight crew to maintain the safe

flight and landing of the airplane.

DATES: Effective November 22, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

22, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle,

Washington 98124–2207. This

information may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 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: Jay

G. Yi, Aerospace Engineer, Systems and

Equipment Branch, ANM–130S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–1013; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Boeing

Model 747–400 series airplanes was

published in the Federal Register on

October 6, 1999 (64 FR 54229). That

action proposed to require removal of

existing inertial reference units (IRU)

and installation of modified IRU’s.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Support for the Proposal

One commenter supports the

proposed rule.

Request To Extend Compliance Time

Three commenters request that the

FAA extend the proposed compliance

time for the installation of modified

IRU’s.

The first commenter states that

sending all its units back to the parts

manufacturer for modification will take

at least two weeks per unit.

Additionally, taking the unmodified

units off all of its airplanes and shipping

them will delay completion of the

installation required by the proposed

AD until receipt of the modified units.

Therefore, the proposed installation

would not be accomplished until

February 2002. The commenter adds

that the dual inertial reference system

(IRS) failure that prompted this

proposal, as stated in the preamble, was

caused by a short circuit in the brake

system control unit (BSCU). The

airplane manufacturer later determined

that the short circuit was due to

moisture ingested into the BSCU, and

released Boeing Service Bulletins 747–

25–3080, Revision 2, dated February 29,

1996 (improves the integrity of the drip

shields), and 747–53–2402, dated

December 21, 1995 (installs protective

panels over the drip shields to protect

them from damage) to address this

condition. The commenter has

completed these modifications, and

notes that these modifications

significantly reduce the likelihood of

water damage to the BSCU. The

commenter states that, considering these

airplane modifications and the realities

of the modification stated above, a twoyear compliance time would be more

realistic.

The second commenter states that 12

months is an unrealistic and

unnecessary compliance time, and

submits the following factors for

consideration: