Federal Register / Vol. 66, No. 14 / Monday, January 22, 2001 / Rules and Regulations 6453

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–SW–67–AD; Amendment

39–12056; AD 2000–26–06]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

Deutschland GMBH Model MBB–BK

117 Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD)

that applies to Eurocopter Deutschland

GMBH (ECD) Model MBB–BK 117

helicopters. That AD currently requires,

before further flight, creating a

component log card or equivalent record

and determining the calendar age and

number of flights on each tensiontorsion (TT) strap. This amendment

establishes a life limit for certain main

rotor TT straps. This amendment is

prompted by an accident in which a

main rotor blade (blade) separated from

an ECD Model MBB–BK 117 helicopter

due to fatigue failure of a TT strap. The

actions specified by this AD are

intended to prevent fatigue failure of a

TT strap, loss of a blade, and subsequent

loss of control of the helicopter.

DATES: Effective February 26, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February

26, 2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from American Eurocopter Corporation,

2701 Forum Drive, Grand Prairie, Texas

75053–4005, telephone (972) 641–3460,

fax (972) 641–3527. 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:

Charles Harrison, Aviation Safety

Engineer, FAA, Rotorcraft Directorate,

Rotorcraft Standards Staff, Fort Worth,

Texas 76193–0110, telephone (817)

222–5128, fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 2000–01–11,

Amendment 39–11509 (65 FR 2017,

January 13, 2000), which applies to ECD

Model MBB–BK 117 helicopters, was

published in the Federal Register on

September 18, 2000 (65 FR 56275). That

action proposed establishing a life limit

for the TT straps of 120 months since

installation on any helicopter or 25,000

flights, whichever occurs first.

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 127

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 16 work hours per

helicopter to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $10,400 per

helicopter. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $1,442,720.

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 39–11509 (65 FR

2017, January 13, 2000), and by adding

a new airworthiness directive (AD),

Amendment 39–12056, to read as

follows:

2000–26–06 Eurocopter Deutschland

GMBH: Amendment 39–12056. Docket

No. 99–SW–67–AD. Supersedes AD

2000–01–11, Amendment 39–11509,

Docket No. 99–SW–60–AD.

Applicability: Model MBB–BK 117 A–1, A–

3, A–4, B–1, B–2, and C–1 helicopters,

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 (d) 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 fatigue failure of a tensiontorsion (TT) strap, loss of a main rotor blade

(blade), and subsequent loss of control of the

helicopter, accomplish the following:

(a) Before further flight,

(1) Remove TT straps, P/N 2604067

(Bendix) or J17322–1 (Lord), from service or

re-identify them as P/N 117–14110 or 117–

14111, respectively, in accordance with the

Accomplishment Instructions, paragraph

2.B.1.2., Eurocopter Deutschland GMBH

Alert Service Bulletin MBB–BK–117 No.

ASB–MBB–BK 117–10–120, Revision 1,

dated August 31, 1999 (ASB). TT straps, P/

N 2604067 (Bendix) or J17322–1 (Lord), are

no longer eligible for installation.

(2) Create a component log card or

equivalent record for each TT strap.

(3) Review the history of the helicopter and

each TT strap. Determine the age since initial

installation on any helicopter (age) and the

number of flights on each TT strap. Enter

both the age and the number of flights for

each TT strap on the component log card or

equivalent record. When the number of

flights is unknown, multiply the number of

hours time-in-service (TIS) by 5 to determine

the number of flights.

(4) Remove any TT strap from service if the

total hours TIS or number of flights and age

cannot be determined.

(b) Before further flight, remove any TT

strap, part number (P/N) 117–14110 or 117–

6454 Federal Register / Vol. 66, No. 14 / Monday, January 22, 2001 / Rules and Regulations

14111, that has been in service 120 months

since initial installation on any helicopter or

accumulated 25,000 flights (a flight is a

takeoff and a landing). Replace the TT strap

with an airworthy TT strap.

(c) This AD revises the Airworthiness

Limitations Section of the maintenance

manual by establishing a life limit for the TT

strap, P/N 117–14110 and 117–14111, of 120

months or 25,000 flights, whichever occurs

first.

(d) 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.

(e) 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.

(f) The modification shall be done in

accordance with the Accomplishment

Instructions, paragraph 2.B.1.2., Eurocopter

Deutschland GMBH Alert Service Bulletin

MBB–BK–117 No. ASB–MBB–BK 117–10–

120, Revision 1, dated August 31, 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

American Eurocopter Corporation, 2701

Forum Drive, Grand Prairie, Texas 75053–

4005, telephone (972) 641–3460, fax (972)

641–3527. 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.

(g) This amendment becomes effective on

February 26, 2001.

Note 3: The subject of this AD is addressed

in the Luftfahrt Bundesamt (Federal Republic

of Germany) AD 1999–284/2, dated

September 1, 1999.

Issued in Fort Worth, Texas, on December

15, 2000.

Henry A. Armstrong,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 01–1585 Filed 1–19–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–03–AD; Amendment

39–12086; AD 2001–02–02]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model DHC–8–200, and –300 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Bombardier Model

DHC–8–200, and –300 series airplanes.

This action requires repetitive

inspections to detect chafing or arcing

damage to the cable/wire and fuel tube

assemblies on the right hand side of

each engine, and replacement with new

components, if necessary. This action

also provides an optional terminating

action for the repetitive inspections

required by this AD. This action is

necessary to prevent chafing of the

cable/wire bundles against the fuel line,

which could result in arcing and a

consequent fire or explosion. This

action is intended to address the

identified unsafe condition.

DATES: Effective February 6, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February 6,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

February 21, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2001–NM–

03–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-

anm-iarcomment@faa.gov. Comments

sent via fax or the Internet must contain

‘‘Docket No. 2001–NM–03–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

Bombardier, Inc., Bombardier Regional

Aircraft Division, 123 Garratt Boulevard,

Downsview, Ontario M3K 1Y5, Canada.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington; or at the FAA,

New York Aircraft Certification Office,

10 Fifth Street, Third Floor, Valley

Stream, New York; or at the Office of the

Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT:

James Delisio, Aerospace Engineer,

Airframe and Propulsion Branch, ANE–

171, FAA, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York

11581; telephone (516) 256–7521; fax

(516) 568–2716.

SUPPLEMENTARY INFORMATION: Transport

Canada Civil Aviation (TCCA), which is

the airworthiness authority for Canada,

recently notified the FAA that an unsafe

condition may exist on certain

Bombardier Model DHC–8–200 and

–300 series airplanes. TCAA advises

that a pinhole in the high pressure fuel

line was detected. Investigation revealed

that the cause of the pinhole was due to

arcing from an adjoining wire. The

arcing occurred approximately four

inches from the fuel-cooled oil cooler.

Although the fuel line and wire are

separated by two cushion clamps, the

cushion clamps can rotate and thereby

allow the wire bundle to chafe against

the fuel line. Such chafing of the wire

bundles could result in arcing and a

consequent fire or explosion.

Explanation of Relevant Service

Information

Bombardier has issued Alert Service

Bulletin A8–73–23, dated November 3,

2000, which describes procedures for

repetitive general visual inspections to

detect chafing or arcing damage to the

cable and the fuel tube assemblies on

the right hand side of each engine, and

replacement with new components, if

necessary. The alert service bulletin also

describes procedures for an optional

modification that entails, among other

things, rerouting the existing wire

harness to the opposite side of the oil

cooler, and shortening and securing the

wire harness, if necessary. That

modification eliminates the need for the

repetitive inspections. TCAA classified

this alert service bulletin as mandatory

and issued Canadian airworthiness

directive CF–2000–33, dated November

14, 2000, in order to assure the

continued airworthiness of these

airplanes in Canada.