Federal Register / Vol. 62, No. 241 / Tuesday, December 16, 1997 / Rules and Regulations 65749

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–SW–44–AD; Amendment

39–10245; AD 97–26–02]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

Deutschland GmbH (ECD) Model BO–

105A, BO–105C, BO–105S, BO–105LS

A–1, and BO–105LS A–3 Helicopters

and Eurocopter Canada Ltd. Model

BO–105LS A–3 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 Eurocopter Deutschland

GmbH (ECD) (Eurocopter Deutschland)

Model BO–105A, BO–105C, BO–105S,

BO–105LS A–1, and BO–105LS A–3

helicopters; and Eurocopter Canada Ltd.

Model BO–105LS A–3 helicopters. This

action requires visual inspections for

cracks in the ribbed area of the main

rotor mast flange (flange). This

amendment is prompted by a report of

an operator discovering a crack in the

flange after experiencing in-flight

vibrations. The actions specified in this

AD are intended to detect cracks in the

flange, which, if not detected, could

result in failure of the flange and

subsequent loss of control of the

helicopter.

DATES: Effective December 31, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

31, 1997.

Comments for inclusion in the Rules

Docket must be received on or before

February 17, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 97–SW–44–

AD, 2601 Meacham Blvd., Room 663,

Fort Worth, Texas 76137.

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 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.

Richard Monschke, Aerospace Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Standards Staff, 2601 Meacham Blvd.,

Fort Worth, Texas 76137, telephone

(817) 222–5116, fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: The

Luftfahrt-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 Model BO–105A, BO–

105C, BO–105S, BO–105LS A–1, and

BO–105LS A–3 helicopters. The Federal

Republic of Germany advises that a

main rotor mast was found to have

cracks of critical magnitude in the area

of the flange. Additionally, Transport

Canada, the airworthiness authority for

Canada, recently notified the FAA that

the same unsafe condition may exist on

Eurocopter Canada Ltd. Model B0–

105LS A–3 helicopters. The cause of the

cracks is under investigation. Until the

cause of the crack has been determined,

the flange must be subjected to an

immediate inspection and repetitive

visual crack inspection at intervals not

to exceed 100 hours time-in-service

until further notice.

Eurocopter Deutschland has issued

Eurocopter Deutschland GmbH Alert

Service Bulletin No. ASB–BO 105–10–

110, dated August 27, 1997, which

specifies visually inspecting the area of

the holes on the underside of the flange

for cracks, especially in the ribbed area

between the holes. The LBA classified

this service bulletin as mandatory and

issued AD 97–275, dated September 25,

1997, in order to assure the continued

airworthiness of these helicopters in the

Federal Republic of Germany.

Eurocopter Canada Ltd. has issued

Eurocopter Canada Ltd. Alert Service

Bulletin No. ASB–BO 105 LS–10–9,

dated September 11, 1997, for similar

inspection. Transport Canada has

classified this service bulletin

mandatory and issued AD CF–97–18,

dated September 30, 1997, in order to

assure the continued airworthiness of

these helicopters in Canada.

This helicopter model is

manufactured in the Federal Republic of

Germany and Canada and is type

certificated for operation in the United

States under the provisions 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 and

Transport Canada have kept the FAA

informed of the situation described

above. The FAA has examined the

findings of the LBA and Transport

Canada, reviewed all available

information, and determined that AD

action is necessary for products of this

type design that are certificated for

operation in the United States.

Since an unsafe condition has been

identified that is likely to exist or

develop on other Eurocopter

Deutschland Model BO–105A, BO–

105C, BO–105S, BO–105LS A–1, and

BO–105LS A–3 helicopters and

Eurocopter Canada Ltd. BO–105LS A–3

helicopters of the same type designs

registered in the United States, this AD

is being issued to detect cracks in the

flange, which, if not detected, could

result in failure of the flange and

subsequent loss of control of the

helicopter. The flange is a part of the

main rotor mast assembly and therefore

a critical component of the flight control

system. Due to the criticality of the

flange to the continued safe flight of the

affected helicopters, and the required

inspection before further flight, this rule

must be issued immediately to correct

an unsafe condition in the affected

helicopters. This AD requires, before

further flight, a visual inspection of the

ribbed area of the flange for cracks using

a 5-power or higher magnifying glass,

and thereafter, repeated visual

inspections at intervals not to exceed

100 hours time-in-service. The actions

are required to be accomplished in

accordance with the service bulletins

described previously.

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

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
65750 Federal Register / Vol. 62, No. 241 / Tuesday, December 16, 1997 / Rules and Regulations

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. 97–SW–44–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, 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:

97–26–02 Eurocopter Deutschland GmbH

(ECD) and Eurocopter Canada LTD.:

Amendment 39–10245. Docket No. 97–

SW–44–AD.

Applicability: Eurocopter Deutschland

GmbH Model BO–105A, BO–105C, BO–105S,

BO–105LS A–1, and BO–105LS A–3

helicopters and Eurocopter Canada Ltd. BO–

105LS A–3 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

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 detect cracks in the main rotor mast

flange (flange), which, if not detected, could

result in failure of the flange and subsequent

loss of control of the helicopter, accomplish

the following:

(a) Before further flight and thereafter at

intervals not to exceed 100 hours time-inservice, visually inspect the flange in the

ribbed area for cracks using a 5-power or

higher magnifying glass in accordance with

paragraphs 2.A.1. and 2.A.2. of the

Accomplishment Instructions of Eurocopter

Deutschland GmbH Alert Service Bulletin

No. ASB–BO 105–10–110, dated August 27,

1997, or Eurocopter Canada Alert Service

Bulletin No. ASB–BO 105 LS–10–9, dated

September 11, 1997, as applicable.

(b) If a crack is found, remove the cracked

main rotor mast and replace it with an

airworthy main rotor mast.

(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, Rotorcraft

Standards Staff, 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, 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 will not be

issued.

(e) The inspection shall be done in

accordance with Eurocopter Deutschland

GmbH Alert Service Bulletin No. ASB–BO

105–10–110, dated August 27, 1997, or

Eurocopter Canada Alert Service Bulletin No.

ASB–BO 105 LS–10–9, dated September 11,

1997, as applicable. These incorporations by

reference were 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 Regional

Counsel, Southwest Region, 2601 Meacham

Blvd., Room 663, Fort Worth, Texas 76137;

or at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

(f) This amendment becomes effective on

December 31, 1997.

Note 3: The subject of this AD is addressed

in Luftfahrt-Bundesamt (Germany) AD 97–

275, dated September 25, 1997, and in

Transport Canada AD CF–97–18, dated

September 30, 1997.

Issued in Fort Worth, Texas, on December

5, 1997.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 97–32720 Filed 12–15–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–SW–45–AD; Amendment

39–10246; AD 97–26–03]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

Deutschland GmbH (ECD) (Eurocopter

Deutschland) Model MBB–BK 117 A–1,

A–3, A–4, B–1, B–2, and C–1

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 Eurocopter Deutschland

Model MBB–BK 117 A–1, A–3, A–4, B–

1, B–2, and C–1 helicopters. This action

requires visual inspections for cracks in

the ribbed area of the main rotor mast

flange (flange). This amendment is

prompted by one report of cracks in a

flange. The actions specified in this AD

are intended to detect cracks in the