34796 Federal Register / Vol. 63, No. 123 / Friday, June 26, 1998 /Rules and Regulations

(c) Record the play measurement on the

equipment log card or equivalent record.

(1) If the play is 0.37 mm or less, comply

with paragraphs (a) or (b) of this AD, as

applicable, at intervals not to exceed 520

hours TIS.

(2) If the play is greater than 0.37 mm and

less than 0.52 mm, comply with paragraphs

(a) or (b) of this AD, as applicable, at

intervals not to exceed 100 hours TIS.

(3) If the play is equal to or greater than

0.52 mm, remove the TGB and replace it with

an airworthy TGB.

(d) Brackets and mounts installed to

perform the requirements of this AD, as

applicable, are to be removed prior to 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, Rotorcraft

Standards Staff, FAA. 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.

(f) Special flight permits will not be issued.

(g) This amendment becomes effective on

July 13, 1998, to all persons except those

persons to whom it was made immediately

effective by Priority Letter AD 98–06–04,

issued March 4, 1998, which contained the

requirements of this amendment.

Note 3: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

(France) AD 97–322–067(AB) and AD 97–

323–079(AB), both dated November 19, 1997.

Issued in Fort Worth, Texas, on June 18,

1998.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 98–17043 Filed 6–25–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–SW–18–AD; Amendment

39–10632; AD 98–09–11]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

Deutschland GmbH Model EC 135

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This document publishes in

the Federal Register an amendment

adopting Airworthiness Directive (AD)

98–09–11 which was sent previously to

all known U.S. owners and operators of

Eurocopter Deutschland GmbH

(Eurocopter) Model EC 135 helicopters

by individual letters. This AD requires,

before further flight, a review of aircraft

records to determine if a tail rotor drive

shaft vibration survey and installation of

a Fenestron Shaft Retrofit Kit have been

accomplished; before further flight, and

thereafter at intervals not to exceed 15

hours time-in-service, inspecting the tail

rotor drive shaft bearing (bearing)

attaching lock plates for bent-open tabs,

and broken or missing slippage marks;

and visually inspecting each bearing

support for cracks. This amendment is

prompted by three reports of loose

bearings and attachment bolts, and one

report of a cracked bearing support.

Excessive vibrations in the tail rotor

drive shaft can loosen attachment bolts

or cause cracking in the bearing

supports. This condition, if not

corrected, could result in loss of drive

to the tail rotor and subsequent loss of

control of the helicopter.

DATES: Effective July 13, 1998, to all

persons except those persons to whom

it was made immediately effective by

priority letter AD 98–09–11, issued on

April 17, 1998, which contained the

requirements of this amendment.

Comments for inclusion in the Rules

Docket must be received on or before

August 25, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 98–SW–18–

AD, 2601 Meacham Blvd., Room 663,

Fort Worth, Texas 76137.

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: On April

17, 1998, the FAA issued priority letter

AD 98–09–11, applicable to Eurocopter

Model EC 135 helicopters, which

requires, before further flight, a review

of aircraft records to determine if a tail

rotor drive shaft vibration survey and

installation of a Fenestron Shaft Retrofit

Kit L 535M3002 882 have been

accomplished. If a tail rotor vibration

survey has not been accomplished or if

a Fenestron Shaft Retrofit Kit has not

been installed, the FAA must be

contacted. Also, before further flight,

and thereafter at intervals not to exceed

15 hours time-in-service, the AD

requires inspecting the bearing attaching

lock plates at each bearing support for

bent-open tabs, and inspecting for

broken or missing slippage marks. If a

bearing attaching lock plate tab is bent

open, or if a slippage mark is broken or

missing, the FAA must be notified.

Finally, the AD requires visually

inspecting each bearing support for

cracks, and if a crack is found, replacing

the bearing support with an airworthy

bearing support. That action was

prompted by three reports of loose

bearings and attachment bolts, and one

report of a cracked bearing support.

Excessive vibrations in the tail rotor

drive shaft can loosen attachment bolts

or cause cracking in the bearing

supports. This condition, if not

corrected, could result in loss of drive

to the tail rotor and subsequent loss of

control of the helicopter.

The Luttfahrt-Bundesamt (LBA),

which is the airworthiness authority for

the Federal Republic of Germany,

recently notified the FAA that an unsafe

condition may exist on Eurocopter

Deutschland GmbH (ECD) Model EC 135

helicopters. The LBA advises that the

loosening of bolt connections at the

bearing supports may lead to a tail rotor

failure and thus to the loss of the

helicopter. The LBA issued AD 1998–

033/5, dated April 6, 1998, applicable to

ECD Model EC 135 helicopters.

The FAA has reviewed Eurocopter EC

135 Alert Service Bulletin No. EC 135–

53A–002, dated December 12, 1997,

which describes procedures for visually

inspecting the bearing supports, and

Eurocopter EC 135 Alert Service

Bulletin No. EC 135–53A–005, Revision

1, dated April 6, 1998, which describes

procedures for measuring vibrations on

the tail rotor drive shaft and

replacement of roller bearing attaching

hardware at bearing locations.

This helicopter model is

manufactured in the Federal Republic of

Germany and is type certificated for

operation in the United States under the

provision of section 21.29 of the Federal

Aviation Regulations (14 CFR 21.29)

and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the LBA has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the LBA,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operations in the United

States.

Since the unsafe condition described

is likely to exist or develop on other

Eurocopter Model EC 135 helicopters of

the same type design, the FAA issued

priority letter AD 98–09–11 to detect

loose bearing attachment bolts, or

cracked bearing supports, which could

result in loss of drive to the tail rotor

and subsequent loss of control of the

helicopter. The AD requires, before
Federal Register / Vol. 63, No. 123 / Friday, June 26, 1998 /Rules and Regulations 34797

further flight, a review of aircraft

records to determine if a tail rotor drive

shaft vibration survey and installation of

a Fenestron Shaft Retrofit Kit L

535M3002 882 have been accomplished.

If a tail rotor vibration survey has not

been accomplished or if a Fenestron

Shaft Retrofit Kit has not been installed,

the FAA must be contacted. Also, before

further flight, and thereafter at intervals

not to exceed 15 hours time-in-service,

the AD requires inspecting the bearing

attaching lock plates at each bearing

support for bent-open tabs, and

inspecting for broken or missing

slippage marks. If a bearing attaching

lock plate tab is bent open, or if a

slippage mark is broken or missing, the

FAA must be notified. Finally, the AD

requires visually inspecting each

bearing support for cracks, and if a crack

is found, replacing the bearing support

with an airworthy bearing support.

The short compliance time involved

is required because the previously

described critical unsafe condition can

adversely affect the controllability of the

helicopter. Therefore, reviewing aircraft

records, inspecting the bearing attaching

lock plates, and visually inspecting each

bearing support for cracks are required

before further flight and this AD must be

issued immediately.

Since it was found that immediate

corrective action was required, notice

and opportunity for prior public

comment thereon were impracticable

and contrary to the public interest, and

good cause existed to make the AD

effective immediately by individual

letters issued on April 17, 1998 to all

known U.S. owners and operators of

Eurocopter Model EC 135 helicopters.

These conditions still exist, and the AD

is hereby published in the Federal

Register as an amendment to section

39.13 of the Federal Aviation

Regulations (14 CFR 39.13) to make it

effective to all persons.

The FAA estimates that 6 helicopters

of U.S. registry will be affected by this

AD, that it will take approximately .5

work hour per helicopter to review

aircraft records and 1 work hour per

helicopter to conduct the required

inspections, and that the average labor

rate is $60 per work hour. Required

parts will be provided at no cost by the

manufacturer. Based on these figures,

the total cost impact of the AD on U.S.

operators is estimated to be $540 to

review the aircraft records and perform

the inspections once on each helicopter

in the U.S. fleet.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this rule by

submitting such written data, views, or

arguments as they may desire.

Communications should identify the

Rules Docket number and be submitted

in triplicate to the address specified

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 98–SW–18–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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

implications to warrant the preparation

of a Federalism Assessment.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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, 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 98–09–11 Eurocopter Deutschland

GmbH: Amendment 39–10632. Docket

No. 98–SW–18–AD.

Applicability: Model EC 135 helicopters,

serial numbers 0005 through 0048,

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 (d) 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 detect loose tail rotor drive shaft

bearing (bearing) attachment bolts, or cracked

bearing supports, which could result in loss

of drive to the tail rotor and subsequent loss

of control of the helicopter, accomplish the

following:

(a) Before further flight, review the

helicopter’s historical records to determine if

a tail rotor drive shaft vibration survey and

the installation of Fenestron Shaft Retrofit Kit

L 535M3002 882 have been accomplished. If

either action has not been accomplished,

contact the Manager, Rotorcraft Standards

Staff, FAA, telephone (817) 222–5110, fax

(817) 222–5961.
34798 Federal Register / Vol. 63, No. 123 / Friday, June 26, 1998 /Rules and Regulations

(b) Before further flight, and thereafter at

intervals not to exceed 15 hours time-inservice (TIS), at each bearing support:

(1) Inspect each bearing attaching lock

plate that was installed with the Fenestron

Shaft Retrofit Kit L 535M3002 882 for bentopen tabs.

(2) Inspect for broken or missing slippage

marks that may indicate looseness or rotation

of attaching hardware.

(3) If a lock plate tab is bent open on

bearing supports A, B, or C (shown in Figure

1), or if slippage marks are broken or missing,

contact the Manager, Rotorcraft Standards

Staff.

BILLING CODE 4910–13–P

BILLING CODE 4910–13–C

(c) Before further flight, and thereafter at

intervals not to exceed 15 hours TIS, using

a 6-power or higher magnifying glass and a

bright light, visually inspect bearing supports

B and C as shown in Figure 1 for cracks. If

a crack is found, replace the bearing support

with an airworthy bearing support.

(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, Rotorcraft

Standards Staff, FAA. 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.

(e) Special flight permits will not be

issued.

(f) This amendment becomes effective on

July 13, 1998, to all persons except those

persons to whom it was made immediately

effective by Priority Letter AD 98–09–11,

issued April 17, 1998, which contained the

requirements of this amendment.

Note 3: The subject of this AD is addressed

in Luftfahrt-Bundesamt (Federal Republic of

Germany) AD 1998–033/5, dated April 6,

1998.

Issued in Fort Worth, Texas, on June 18,

1998.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 98–17023 Filed 6–25–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–SW–65–AD; Amendment

39–10619; AD 98–13–28]

RIN 2120–AA64

Airworthiness Directives; Agusta

S.p.A. Model A109C and A109K2

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to Agusta S.p.A. (Agusta)

Model A109C and A109K2 helicopters.

This action requires a one-time

inspection of each tail rotor blade

(blade) for debonding, and if debonding

exists which exceeds certain limits,