62280 Federal Register / Vol. 65, No. 202 / Wednesday, October 18, 2000 / Rules and Regulations

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–SW–35–AD; Amendment

39–11929; AD 2000–20–17]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France Model AS332C, L, and L1

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) for

Eurocopter France (ECF) Model

AS332C, L, and L1 helicopters. This AD

requires inspecting the horizontal

stabilizer spar tube (spar tube) for

corrosion, hardness, cracks, and

scratches, and if necessary, replacing

any unairworthy spar tube and bushing

with an airworthy spar tube and

bushing. This amendment is prompted

by the loss of a horizontal stabilizer in

flight due to a spar tube failure. The

actions specified by this AD are

intended to prevent failure of the spar

tube, separation of the horizontal

stabilizer and impact with the main or

tail rotor, 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 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: Jim

Grigg, Aviation Safety Engineer, FAA,

Rotorcraft Directorate, Regulations

Group, Fort Worth, Texas 76193–0111,

telephone (817) 222–5490, fax (817)

222–5961.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

which applied to the ECF Model

AS332C, L, and L1 helicopters was

published in the Federal Register on

July 14, 2000 (65 FR 43720). That action

proposed to require inspecting any spar

tube installed on certain horizontal

stabilizers for corrosion, hardness,

cracks, or scratches. Replacing the spar

tube and bushing, as necessary, with an

airworthy spar tube and bushing was

also proposed.

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 3 helicopters

of U.S. registry will be affected by this

AD, that it will take approximately 40

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

$1,000 per helicopter. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$10,200.

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:

2000–20–17 Eurocopter France:

Amendment 39–11929. Docket No. 99–

SW–35–AD.

Applicability: Model AS332C, L, and L1

helicopters with horizontal stabilizer spar

tube (spar tube), part number (P/N) 330A13–

2024–01, –02, –03, or –04, installed on

horizontal stabilizer, P/N 332A13–1000–00,

–01, –02, –03 or 332A13–1040–00, or –01,

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

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent failure of the spar tube,

separation of the horizontal stabilizer and

impact with the main or tail rotor, and

subsequent loss of control of the helicopter,

accomplish the following:

(a) For helicopters on which the spar tube

composite bushing (bushing), P/N 330A13–

2024–31, has been replaced and since

replacement has accumulated:

(1) Less than 1400 hours time-in-service

(TIS) or less than 30 calendar months:

(i) Prior to accumulating 1600 hours TIS or

32 calendar months, whichever occurs first,

and thereafter at intervals not to exceed

(NTE) 3000 hours TIS or 72 calendar months,

whichever occurs first, inspect the spar tube

in accordance with (IAW) the

Accomplishment Instructions, paragraph

2.B.1.1 and 2.B.2. of Eurocopter France

Service Bulletin No. 01.00.57, Revision 1,

dated November 24, 1999 (SB).

(A) If the spar tube passes the hardness

inspection of paragraph 2.B.1.1 of the SB and

the scratch, corrosion, and crack inspection

of paragraph 2.B.2. of the SB, replace the

bushing with a new bushing, before further

flight.

(B) If the spar tube fails either the hardness

inspection of paragraph 2.B.1.1 of the SB or

the scratch, corrosion, or crack inspection of

paragraph 2.B.2. of the SB, replace the spar

tube with an airworthy spar tube before

further flight.

Federal Register / Vol. 65, No. 202 / Wednesday, October 18, 2000 / Rules and Regulations 62281

(ii) Before installing any replacement spar

tube that has previously been installed on

any helicopter, inspect it IAW the

Accomplishment Instructions, paragraphs

2.B.1.1 and 2.B.2. of the SB.

(2) 1400 or more hours TIS or 30 or more

calendar months:

(i) Within 200 hours TIS or 2 calendar

months, whichever occurs first, and

thereafter at intervals NTE 3000 hours TIS or

72 calendar months, whichever occurs first,

inspect the spar tube IAW the

Accomplishment Instructions, paragraphs

2.B.1.1 and 2.B.2. of the SB.

(A) If the spar tube passes the hardness

inspection of paragraph 2.B.1.1 of the SB and

the scratch, corrosion, and crack inspection

of paragraph 2.B.2 of the SB, replace the

bushing with a new bushing before further

flight.

(B) If the spar tube fails either the hardness

inspection of paragraph 2.B.1.1 of the SB or

the scratch, corrosion, or crack inspection of

paragraph 2.B.2 of the SB, replace the spar

tube with an airworthy spar tube before

further flight.

(ii) Before installing any replacement spar

tube that has previously been installed on

any helicopter, inspect it IAW the

Accomplishment Instructions, paragraphs

2.B.1.1 and 2.B.2. of the SB.

(b) For all spar tubes:

(1) With less than 7500 hours TIS or 144

calendar months since original installation:

(i) Prior to accumulating 7500 hours TIS or

144 calendar months, remove the spar tube

and inspect IAW the Accomplishment

Instructions, paragraphs 2.B.1.1 and 2.B.2. of

the SB.

(ii) After accomplishing the requirements

of paragraph (b)(1)(i) of this AD, install an

airworthy spar tube before further flight.

Before installing any replacement spar tube

that has been previously installed in any

helicopter, inspect it IAW the

Accomplishment Instructions, paragraphs

2.B.1.1 and 2.B.2. of the SB.

(2) With 7500 or more hours TIS or 144 or

more calendar months since original

installation:

(i) Within 500 hours TIS or 12 calendar

months, whichever occurs first, remove the

spar tube and inspect IAW the

Accomplishment Instructions, paragraphs

2.B.1.1 and 2.B.2. of the SB.

(ii) After accomplishing the requirements

of paragraph (b)(2)(i) of this AD, install an

airworthy spar tube before further flight.

Before installing any replacement spar tube

that has been previously installed in any

helicopter, inspect it IAW the

Accomplishment Instructions, paragraph

2.B.1.1 and 2.B.2. of the SB.

(3) After accomplishing the requirements

of either paragraph (b)(1) or (b)(2) of this AD,

as applicable, thereafter, at intervals NTE

7500 hours TIS or 144 calendar months,

whichever occurs first, remove the spar tube

and inspect IAW the Accomplishment

Instructions, paragraphs 2.B.1.1 and 2.B.2. of

the SB.

(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

a 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 inspections shall be done in

accordance with the Accomplishment

Instructions, paragraphs 2.B.1.1 and 2.B.2., in

Eurocopter France Service Bulletin No.

01.00.57, Revision 1, dated November 24,

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.

(f) This amendment becomes effective on

November 22, 2000.

Note 3: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

(France) AD 1999–039–073(A)R1, dated

December 29, 1999.

Issued in Fort Worth, Texas, on September

29, 2000.

Henry A. Armstrong,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 00–26235 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–228–AD; Amendment

39–11756; AD 2000–11–08]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 and 767 Series Airplanes

Powered by General Electric Model

CF6–80C2 Series Engines; Correction

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This document corrects a

typographical error that appeared in

airworthiness directive (AD) 2000–11–

08, amendment 39–11756, that was

published in the Federal Register on

June 1, 2000 (65 FR 34935). The

typographical error resulted in a

reference to an incorrect fuel

specification. That AD is applicable to

certain Boeing Model 747 and 767 series

airplanes. That AD supersedes an earlier

airworthiness directive to require

revising the FAA-approved Airplane

Flight Manual (AFM) to prohibit the use

of certain fuels; and either replacing an

existing placard with a new placard, or

replacing all dribble flow fuel nozzles

(DFFN) with standard fuel nozzles,

which terminates the requirements for

the new placard and AFM revision. That

AD also includes identical requirements

applicable to airplanes on which

standard fuel nozzles are not installed.

DATES: Effective July 6, 2000.

FOR FURTHER INFORMATION CONTACT: Ed

Hormel, Aerospace Engineer,

Propulsion Branch, ANM–140S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2681; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION:

Airworthiness Directive (AD) 2000–11–

08, amendment 39–11756, applicable to

certain Boeing Model 747 and 767 series

airplanes, was published in the Federal

Register on June 1, 2000 (65 FR 34935).

That AD supersedes AD 98–08–23,

amendment 39–10472 (63 FR 18817,

April 16, 1998) to require revising the

FAA-approved Airplane Flight Manual

(AFM) to prohibit the use of certain

fuels; and either replacing an existing

placard with a new placard, or replacing

all dribble flow fuel nozzles (DFFN)

with standard fuel nozzles, which

terminates the requirements for the new

placard and AFM revision. That AD also

includes identical requirements

applicable to airplanes on which

standard fuel nozzles are not installed.

As published, AD 2000–11–08

contains an erroneous fuel specification

in paragraphs (a)(1)(i) and (c)(1) of that

AD. Those paragraphs incorrectly

reference MIL–T–83113, which is a

specification that does not exist. The

correct reference is MIL–T–83133.

Since no other part of the regulatory

information has been changed, the final

rule is not being republished.

Accordingly, in FR Doc. 00–13447

published June 1, 2000 (65 FR 34935),

make the following corrections:

The effective date of this AD remains

July 6, 2000.

§ 39.13 [Corrected]

1. On page 34937, in the second

column, paragraph (a)(1)(i) of AD 2000–

11–08 is corrected to read as follows:

AD 2000–11–08

* * * * *

(a) * * *