19346 Federal Register / Vol. 60, No. 74 / Tuesday, April 18, 1995 / Rules and Regulations

series airplanes, and Model Avro 146–RJ70A,

–RJ85A, and –RJ100A series airplanes; as

listed in Avro International Aerospace

Service Bulletin S.B. 57–33, Revision 3,

dated September 16, 1994; certificated in any

category.

Note 1: This AD applies to each airplane

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

airplanes 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 airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent fuel leaks and a subsequent fire,

accomplish the following:

(a) For airplanes listed in British Aerospace

Service Bulletin SB 57–33, dated August 31,

1989: Within 12 months after May 21, 1990

(the effective date of AD 90–08–15,

amendment 39–6577), visually inspect for

integrity of nuts and tightness of bolts, and/

or fuel leaks of the outboard vertical row of

fasteners at the left- and right-hand of the

rear spar root joint attachment fittings, in

accordance with British Aerospace Service

Bulletin 57–33, dated August 31, 1989;

Revision 1, dated October 29, 1993; Revision

2, dated February 16, 1994; or Revision 3,

dated September 16, 1994. Repeat the

inspection thereafter at intervals not to

exceed 4,000 landings.

(1) If no defects are found, prior to further

flight, reinstall the left- and right-hand wingto-fuselage fairing panels in accordance with

the service bulletin.

(2) If any defect is found, prior to further

flight, repair suspect and leaking fasteners, in

accordance with the service bulletin.

(b) For airplanes listed in Avro

International Aerospace Service Bulletin S.B.

57–33, Revision 3, dated September 16, 1994,

and not subject to paragraph (a) of this AD:

Within 12 months after the effective date of

this AD, visually inspect for integrity of nuts

and tightness of bolts, and/or fuel leaks of the

outboard vertical row of fasteners at the leftand right-hand of the rear spar root joint

attachment fittings, in accordance with Avro

International Aerospace Service Bulletin S.B.

57–33, Revision 1, dated October 29, 1993;

Revision 2, dated February 16, 1994; or

Revision 3, dated September 16, 1994. Repeat

the inspection thereafter at intervals not to

exceed 4,000 landings.

(1) If no defects are found, prior to further

flight, reinstall the left- and right-hand wingto-fuselage fairing panels in accordance with

the service bulletin.

(2) If any defect is found, prior to further

flight, repair suspect and leaking fasteners in

accordance with the service bulletin.

(c) Modification of the rear spar root joint

attachment fittings at wing rib 2 in

accordance with Avro International

Aerospace Service Bulletin S.B. 57–33,

Revision 1, dated October 29, 1993; Revision

2, dated February 16, 1994; or Revision 3,

dated September 16, 1994; constitutes

terminating action for the repetitive visual

inspections required by this AD.

(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,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(e) 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 airplane to

a location where the requirements of this AD

can be accomplished.

(f) The actions done in accordance with

British Aerospace Service Bulletin SB 57–33,

dated August 31, 1989, including Appendix

A; Avro International Aerospace Service

Bulletin S.B. 57–33, Revision 1, dated

October 29, 1993; Avro International

Aerospace Service Bulletin S.B. 57–33,

Revision 2, dated February 16, 1994; or Avro

International Aerospace Service Bulletin S.B.

57–33, Revision 3, dated September 16, 1994;

as applicable. Revision 3 of Avro

International Aerospace Service Bulletin S.B.

57–33 contains the following list of effective

pages:

Page No.

Revision

level

shown on

page

Date shown

on page

1–3 ....................... 3 Sept. 16,

1994.

4–6 ....................... 2 February 16,

1994.

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 British Aerospace Holdings, Inc., Avro

International Aerospace Division, P.O. Box

16039, Dulles International Airport,

Washington, DC 20041–6039. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(g) This amendment becomes effective on

May 18, 1995.

Issued in Renton, Washington, on April 5,

1995.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–8825 Filed 4–17–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–SW–06–AD; Amendment

39–9201; AD 95–08–12]

Airworthiness Directives; Eurocopter

Deutschland GmbH (ECD) Model MBBBK 117 A–1, A–3, A–4, B–1, B–2, and

C–1 Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Eurocopter Deutschland

GmbH (ECD) Model MBB-BK 117 A–1,

A–3, A–4, B–1, B–2, and C–1

helicopters, that requires a modification

of the latches on the transmission and

engine cowling access doors. This

amendment is prompted by five

occurrences of an engine or

transmission cowling access door

becoming loose in flight. The actions

specified by this AD are intended to

prevent the transmission and engine

cowling access doors from opening in

flight, being struck by the main rotor

blade, and subsequently, separating

from the helicopter and being ingested

by the main rotor or tail rotor system

resulting in a loss of control of the

helicopter.

DATES: Effective May 23, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 23,

1995.

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

Assistant Chief Counsel, 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: A

proposal to amend part 39 of the Federal
Federal Register / Vol. 60, No. 74 / Tuesday, April 18, 1995 / Rules and Regulations 19347

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to Eurocopter

Deutschland GmbH (ECD) Model MBBBK 117 helicopters was published in the

Federal Register on September 13, 1994

(59 FR 46946). That action proposed to

require replacing the current latches

with those having positive locks,

relocating certain latches, and installing

additional locks on the transmission

and engine cowling access doors within

the next 150 hours time-in-service.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

One commenter states that some of

the language in the AD should be

changed. Specifically, the commenter

believes that the words ‘‘access door

becoming loose in flight’’ and ‘‘resulting

in loss of control of the helicopter’’,

which were used to describe the unsafe

condition, are misleading. According to

the commenter, use of proper locking

procedures will prevent the doors from

becoming loose in flight. Also, there

have not been any incidents in which

there has been a loss of control of the

helicopter. The FAA does not concur.

The FAA has determined that the

current latches can become worn and

loose and subsequently fail, even if

properly latched. Thus far, loose

cowling doors have only caused damage

to main rotor blades. However, the FAA

has determined that main rotor blade

damage as well as other resultant

damage from loose cowling doors could

result in loss of control of the

helicopter.

After a careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed, except

that the words ‘‘cowlings, fire walls, and

fuselage’’ were added to paragraph (a) of

the AD to clarify that, in addition to

modifying the transmission and engine

cowlings, the appropriate mating

components also needed to be installed

on the cowlings, firewalls, and fuselage.

Additionally, the helicopter models

were listed to avoid confusion regarding

the applicability of the rule. Finally, the

FAA has revised the proposed estimated

average labor rate from $55 per work

hour to an estimated average labor rate

of $60 per work hour in the preamble

portion of this final rule. This revision

will increase the estimated total cost of

the AD from $390,474 to $418,824. The

FAA has determined that these changes

will neither increase the economic

burden on any operator nor increase the

scope of the AD.

The FAA estimates that 126

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 45 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 $624 per

helicopter. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $418,824.

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.

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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive to

read as follows:

95–08–12 Eurocopter Deutschland GmbH

(ECD): Amendment 39–9201. Docket No.

94–SW–06–AD.

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

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

numbers 7001 through 7201, certificated in

any category.

Compliance: Required as indicated, unless

accomplished previously.

To prevent the transmission and engine

cowling access doors from opening in flight,

being struck by the main rotor blade, and

subsequently, separating from the helicopter

and being ingested by the main rotor or tail

rotor system resulting in a loss of control of

the helicopter, accomplish the following:

(a) Within the next 150 hours time-inservice, remove the left-hand and right-hand

transmission and engine cowlings without

removing the transmission and engine

cowling access doors that are installed on the

transmission and engine cowlings, and

modify the access door latches, cowlings, fire

walls, and fuselage in accordance with the

Work Procedure contained in the

Accomplishment Instructions of MBBHelicopters Alert Service Bulletin ASB–

MBB–BK 117–20–104, Revision 1, dated

December 8, 1989.

(b) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used when approved by the Manager,

Rotorcraft Standards Staff, FAA, Rotorcraft

Directorate. 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: Information concerning the existence

of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft Standards Staff.

(c) 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.

(d) The modification shall be done in

accordance with MBB-Helicopters Alert

Service Bulletin ASB–MBB–BK 117–20–104,

Revision 1, dated December 8, 1989. 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 Assistant Chief Counsel, 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.

(e) This amendment becomes effective on

May 23, 1995.

Issued in Fort Worth, Texas, on April 10,

1995.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 95–9236 Filed 4–17–95; 8:45 am]

BILLING CODE 4910–13–P