Federal Register / Vol. 63, No. 110 /Tuesday, June 9, 1998 /Rules and Regulations 31347

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–321–AD; Amendment

39–10444; AD 98–12–17]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace Model Viscount 744, 745,

745D, and 810 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Direct final rule; confirmation of

effective date.

SUMMARY: This document confirms the

effective date of a direct final rule

published on April 2, 1998, which

adopted a new airworthiness directive

(AD) that is applicable to all British

Aerospace Model Viscount 744, 745,

745D, and 810 series airplanes. This

amendment requires repetitive

inspections to detect cracking and

corrosion of components of the engine

nacelle subframe structure, and

corrective action, if necessary; and

replacement of any component that has

reached its life limit (safe life) with a

new or serviceable component. This

amendment is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified in this AD are intended to

ensure periodic replacement of certain

engine nacelle subframe components

that have reached their maximum life

limits. Cracking and corrosion of these

components, if not detected and

corrected in a timely manner, could

result in reduced structural integrity of

the engine nacelle subframe structure,

separation of the engine from the

airframe, and reduced controllability of

the airplane.

EFFECTIVE DATE: The direct final rule

published at 63 FR 16111 is effective on

July 1, 1998.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: The FAA

published this direct final rule with

request for comments in the Federal

Register on April 2, 1998 (63 FR 16111).

The FAA uses the direct final

rulemaking procedure for a noncontroversial rule where the FAA

anticipates that there will be no adverse

public comment. This direct final rule

advised the public that no adverse

comments were anticipated, and that

unless a written adverse comment, or a

written notice of intent to submit such

an adverse comment, was received

within the comment period, the

regulation would become effective on

July 1, 1998. No adverse comments were

received, and thus this document

confirms that this final rule will become

effective on that date, with the

airworthiness directive (AD) number

shown at the beginning of this

document.

Issued in Renton, Washington, on June 2,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–15133 Filed 6–8–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–SW–07–AD; Amendment

39–10571; AD 98–12–15]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France Model AS 332C, L, L1, and L2

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Eurocopter France Model

AS 332C, L, L1, and L2 helicopters that

requires visually inspecting the

intermediate gearbox-to-structure

attachment stirrup (stirrup) front tabs

for cracks, and if a crack is discovered,

removing the intermediate gearbox and

replacing it with an airworthy

intermediate gearbox; and inspecting for

the conformity of the attachment parts.

This amendment is prompted by five

reports of failure of the two stirrup tabs.

The actions specified by this AD are

intended to prevent failure of the

intermediate gearbox stirrup front tabs,

loss of anti-torque drive, and subsequent

loss of control of the helicopter.

DATES: Effective July 14, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 14,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from American Eurocopter Corporation,

2701 Forum Drive, Grand Prairie, Texas

75053–4005. 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: Mr.

Scott Horn, Aerospace Engineer, FAA,

Rotorcraft Directorate, Rotorcraft

Standards Staff, 2601 Meacham Blvd.,

Fort Worth, Texas 76137, telephone

(817) 222–5125, fax (817) 222–5961.

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 Eurocopter France

Model AS 332C, L, L1, and L2

helicopters was published in the

Federal Register on April 7, 1998 (63 FR

16916). That action proposed to require

visually inspecting the stirrup front tabs

for cracks, and if a crack is discovered,

removing the intermediate gearbox and

replacing it with an airworthy

intermediate gearbox; and inspecting for

the conformity of the attachment parts.

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 an

editorial change in the ‘‘Applicability’’

section of the AD where the word ‘‘and’’

has been changed to ‘‘or.’’ This change

is to make it clear that this AD applies

to the affected model helicopters when

either of the three part numbers is

installed. The FAA has determined that

this change will neither increase the

economic burden on an operator nor

increase the scope of the AD.

The FAA estimates that 4 helicopters

of U.S. registry will be affected by this

AD, that it will take approximately 0.25

work hours to inspect the tabs, and 3

work hours to inspect for conformity,

and that the average labor rate is $60 per

work hour. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $780.

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism
31348 Federal Register / Vol. 63, No. 110 /Tuesday, June 9, 1998 /Rules and Regulations

implications to warrant the preparation

of a Federalism Assessment.

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:

AD 98–12–15 Eurocopter France:

Amendment 39–10571. Docket No. 98–

SW–07–AD.

Applicability: Model AS 332C, L, L1, and

L2 helicopters, with intermediate gearboxes

(IGB), part numbers (P/N) 332A35–0002 all

dash numbers, 332A35–0010 all dash

numbers, or 332A35–0011–01, installed,

except those IGBs modified in accordance

with MOD 0761049 or MOD 0761050,

certificated in any category.

Note 1: This AD applies to each helicopter

identified in the preceding applicability

provision, regardless of whether it has been

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 use the authority

provided in paragraph (c) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any helicopter

from the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent failure of the IGB-to-structure

attachment stirrup (stirrup) front tabs, loss of

anti-torque drive, and subsequent loss of

control of the helicopter, accomplish the

following:

(a) Before the first flight of each day,

perform a visual inspection of the stirrup

front tabs for cracks in accordance with

paragraph 2.B.1) of the Accomplishment

Instructions in Eurocopter France AS 332

Service Bulletin 01.00.47, Revision No. 1,

dated September 10, 1997 (SB). If a crack is

found, remove the IGB and replace it with an

airworthy IGB before further flight.

Completion of the conformity procedure

contained in paragraph 2.B.2.1.3) of the SB

is terminating action for the requirement of

this AD to inspect for cracks prior to the first

flight of each day.

(b) Within 100 hours time-in-service (TIS),

inspect the two front attaching assemblies

securing the stirrup of the IGB to the angle

bracket of the structure (attachment

assembly) for thickness of the stirrup front

tabs in accordance with paragraph 2.B.2) of

the SB.

(1) If the attachment assembly meets the

conformity requirements of either paragraph

2.B.2.1.1) or 2.B.2.1.2) of the SB, reassemble

the attachment assembly in accordance with

paragraph 2.B.2.1.3) of the SB.

(2) If the attachment assembly does not

meet the conformity requirements of either

paragraph 2.B.2.1.1) or 2.B.2.1.2) of the SB,

replace it with an attachment assembly

which does meet the conformity

requirements of either of those paragraphs.

Install the attachment assembly hardware in

accordance with 2.B.2.1.3) of the SB.

(3) If a crack is discovered in the stirrup

front tabs as a result of the conformity

inspection, remove the IGB and replace it

with an airworthy IGB before further flight.

(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, FAA,

Rotorcraft Directorate, Rotorcraft Standards

Staff. Operators shall submit their requests

through an FAA Principal Maintenance

Inspector, who may concur or comment and

then send it to the Manager, Rotorcraft

Standards Staff.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft Standards Staff.

(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 and replacement, if

necessary, shall be done in accordance with

Eurocopter France AS 332 Service Bulletin

01.00.47, Revision No. 1, dated September

10, 1997. 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. 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

July 14, 1998.

Note 3: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

(France) AD 96–263–060(AB)R1 for

Eurocopter France (ECF) Model AS 332C, L,

and L1 helicopters, and AD 96–262–

004(AB)R1 for ECF Model AS 332L2

helicopters, both dated November 5, 1997.

Issued in Fort Worth, Texas, on May 29,

1998.

Henry A. Armstrong,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 98–15124 Filed 6–8–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–SW–07–AD; Amendment

39–10572; AD 98–12–16]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France Model SA 330F, G, and J

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Eurocopter France Model

SA 330F, G, and J helicopters that

requires visually inspecting the

intermediate gearbox (IGB) fairing safety

stop (safety stop) for cracks, crazing, or

edge wear, and if a crack, crazing, or

edge wear exceeds the established

limits, replacing the safety stop; and,

inspecting to ensure that the inclined

drive shaft fairing hinge pin is properly

locked. A terminating action is provided

in the AD by installing an additional

safety stop on the IGB fairing. This

amendment is prompted by one report

of an accident involving the loss of the

inclined drive shaft fairing. The actions

specified by this AD are intended to

prevent loss of the inclined drive shaft

fairing, impact with the tail rotor, and

subsequent loss of control of the

helicopter.

DATES: Effective July 14, 1998.

The incorporation by reference of

certain publications listed in the