3796 Federal Register / Vol. 65, No. 16 / Tuesday, January 25, 2000 / Rules and Regulations

Note 5: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

Special Flight Permits

(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 airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(d) Except as provided by paragraphs (a)(1)

and (a)(2) of this AD, the actions shall be

done in accordance with McDonnell Douglas

Service Bulletin DC8–57–100, Revision 01,

dated August 26, 1998. 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 Boeing Commercial Aircraft

Group, Long Beach Division, 3855 Lakewood

Boulevard, Long Beach, California 90846,

Attention: Technical Publications Business

Administration, Dept. C1–L51 (2–60). Copies

may be inspected at the FAA, Transport

Airplane Directorate, 1601 Lind Avenue,

SW., Renton, Washington; or at the FAA,

Transport Airplane Directorate, Los Angeles

Aircraft Certification Office, 3960 Paramount

Boulevard, Lakewood, California; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(e) This amendment becomes effective on

February 29, 2000.

Issued in Renton, Washington, on January

13, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–1368 Filed 1–24–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–SW–74–AD; Amendment

39–11517; AD 2000–01–19]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

Deutschland GMBH Model EC 135 P1

and EC 135 T1 Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD)

applicable to Eurocopter Deutschland

GMBH (ECD) Model EC 135 P1 and EC

135 T1 helicopters. This action requires

inspecting main rotor expansion bolt

safety wires, bolt heads, and bolt nuts;

replacing any unairworthy expansion

bolt with a hexagon bolt; and, as

necessary, replacing any bolt nut before

further flight. This AD also requires

replacing each expansion bolt,

regardless of condition, no later than

January 31, 2000. This amendment is

prompted by reports of main rotor blade

expansion bolt nuts becoming loose.

This condition, if not corrected, could

result in severe vibration during flight

and subsequent loss of control of the

helicopter.

DATES: Effective February 4, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February 4,

2000.

Comments for inclusion in the Rules

Docket must be received on or before

March 27, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 99–SW–74–

AD, 2601 Meacham Blvd., Room 663,

Fort Worth, Texas.

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,

Room 663, Fort Worth, Texas.

FOR FURTHER INFORMATION CONTACT:

Richard A. Monschke, Aerospace

Engineer, FAA, Rotorcraft Directorate,

Rotorcraft Standards Staff, Fort Worth,

Texas 76193–0110, telephone (817)

222–5116, fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: LuftfahrtBundesamt (LBA), the airworthiness

authority for the Federal Republic of

Germany, notified the FAA that an

unsafe condition may exist on Model EC

135 P1 and EC 135 T1 helicopters. The

LBA advises that severe vibrations

occurred during a helicopter flight due

to an expansion bolt nut becoming

loose.

ECD has issued Alert Service Bulletin

EC135–62A–005, Revision 1, dated

November 16, 1999 (ASB). The ASB

specifies inspecting the safety wire, bolt

head, and bolt nut for the extent of

thread protrusion of the expansion bolt

through the end of the nut; replacing the

expansion bolt by a hexagon bolt as

necessary; and replacing the nut as

necessary. In addition, all hexagon bolts

must replace all expansion bolts no later

than January 31, 2000. The LBA

classified this ASB as mandatory and

issued AD 1999–264, dated July 2, 1999,

to ensure the continued airworthiness of

these helicopters in the Federal

Republic of Germany.

These helicopter models are

manufactured in the Federal Republic of

Germany and are 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 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 operation in the United

States.

Since an unsafe condition has been

identified that is likely to exist or

develop on other ECD Model EC 135 P1

and EC 135 T1 helicopters of the same

type designs registered in the United

States, this AD is being issued to

prevent a main rotor blade expansion

bolt from becoming loose, severe

vibration during flight, and subsequent

loss of control of the helicopter. This

AD requires, before further flight and at

intervals not to exceed 15 hours time-inservice (TIS), inspecting the main rotor

blade expansion bolt safety wire, bolt

head, and bolt nut for the extent of

thread protrusion of the expansion bolt

through the end of the nut; replacing

any unairworthy expansion bolt with a

hexagon bolt; and replacing the nut as

necessary. The AD also requires

replacing all expansion bolts, part

number (P/N) L621M1010 223, with

hexagon bolts, P/N L621M1010 222,

before further flight after January 31,

2000. The actions are required to be

accomplished in accordance with the

ASB described previously. The short

compliance time involved is required

because the previously described

critical unsafe condition can adversely

affect the structural integrity of the

helicopter. Therefore, inspecting the

main rotor blade expansion bolt safety

wire, bolt head, and bolt nut; replacing

any unairworthy expansion bolt with a

hexagon bolt; and replacing the nut as

necessary is required before further

flight and this AD must be issued

immediately.

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.

The FAA estimates that 14 helicopters

will be affected by this AD, that it will

take approximately 10 work hours to

Federal Register / Vol. 65, No. 16 / Tuesday, January 25, 2000 / Rules and Regulations 3797

accomplish inspecting and replacing the

parts, and that the average labor rate is

$60 per work hour. The ECD ASB states

that the replacement parts kit, P/N EC

135–62A–005–2.C, will be provided on

request to ECD at no cost. Based on

these figures, the total cost impact of the

AD on U.S. operators is estimated to be

$8,400.

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. 99–SW–74–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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 proposal does not

have federalism implications under

Executive Order 13132.

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:

AD 2000–01–19 Eurocopter Deutschland

GMBH: Amendment 39–11517. Docket

No. 99–SW–74–AD.

Applicability: Model EC 135 P1 and EC 135

T1 helicopters, with main rotor blades up to

and including serial number 834, installed,

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 (d) 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 a main rotor blade expansion

bolt nut becoming loose, causing severe

vibration during flight, and subsequent loss

of control of the helicopter, accomplish the

following:

(a) Before further flight and thereafter at

intervals not to exceed 15 hours time-inservice, visually inspect the main rotor blade

expansion bolt safety wire, bolt head, and

bolt nut in accordance with the

Accomplishment Instructions, paragraph

3.A., steps (1), (2), (3), (4), and (6) of

Eurocopter Deutschland GMBH (ECD) Alert

Service Bulletin EC 135–62A–005, Revision

1, dated November 16, 1999 (ASB). If the

safety wire is improperly fitted, the bolt head

is worn, the expansion bolt thread does not

protrude through the end of the nut, the bolt

head has metallic abrasions, the nut is loose,

or the nut has metallic abrasions, before

further flight, replace the expansion bolt, part

number (P/N) L621M1010 223, with a

hexagon bolt, P/N L621M1010 222, and, as

necessary, replace the nut in accordance with

paragraph 3.B. of the ASB.

(b) Replace all expansion bolts, P/N

L621M1010 223, with hexagon bolts, P/N

L621M1010 222, and, as necessary, replace

the nuts before flight after January 31, 2000.

(c) Replacing the expansion bolts with

hexagon bolts and replacing the nuts, as

necessary, constitutes terminating action for

the requirements of 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, Regulations

Group, 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, 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.

(e) Special flight permits will not be

issued.

(f) The inspection and replacement of the

main rotor blade bolts shall be done in

accordance with the Accomplishment

Instructions, paragraph 3.A., Eurocopter

Deutschland GMBH Alert Service Bulletin EC

135–62A–005, Revision 1, dated November

16, 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, Room 663, Fort Worth,

Texas; or at the Office of the Federal Register,

800 North Capitol Street, NW., suite 700,

Washington, DC.

(g) This amendment becomes effective on

February 4, 2000.

Note 3: The subject of this AD is addressed

in Luftfahrt-Bundesamt (the Federal Republic

of Germany) AD 1999–264, dated July 2,

1999.

3798 Federal Register / Vol. 65, No. 16 / Tuesday, January 25, 2000 / Rules and Regulations

Issued in Fort Worth, Texas, on January 11,

2000.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 00–1369 Filed 1–24–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–223–AD; Amendment

39–11520; AD 2000–02–02]

RIN 2120–AA64

Airworthiness Directives; Short

Brothers Model SD3–60 SHERPA,

SD3–SHERPA, and SD3–30 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Short Brothers Model

SD3–60 SHERPA and SD3–SHERPA

series airplanes, and certain Model

SD3–30 series airplanes, that requires

replacement of existing oxygen system

‘‘O’’ rings with improved wear-resistant

‘‘O’’ rings. This amendment is prompted

by issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by this AD are

intended to prevent the loss of oxygen

from the aircraft oxygen system, which

could result in an insufficient supply of

oxygen being provided to the airplane

flight crew and passengers in the event

of an emergency.

DATES: Effective February 29, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February

29, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Short Brothers, Airworthiness &

Engineering Quality, P.O. Box 241,

Airport Road, Belfast BT3 9DZ,

Northern Ireland. This information may

be examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

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: 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 all Short Brothers

Model SD3–60 SHERPA, SD3–SHERPA,

and SD3–30 series airplanes was

published in the Federal Register on

October 6, 1999 (64 FR 54237). That

action proposed to require replacement

of existing oxygen system ‘‘O’’ rings

with improved wear-resistant ‘‘O’’ rings.

Comment Received

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comment received.

One commenter requests that the

applicability of the proposed AD be

revised to include only those Model

SD3–30 series airplanes on which an

oxygen system is installed. The

commenter states that only one variant

of these airplanes was delivered in this

configuration, and provides a list of the

applicable serial numbers. The

commenter notes that these serial

numbers are also listed in Shorts

Service Bulletin SD330–35–1, dated

February 25, 1999, which is referenced

as the appropriate source of service

information in the proposed AD.

The FAA concurs that the

requirements of the AD are applicable

only to those airplanes on which an

oxygen system is installed. The FAA has

limited the applicability for Model SD3–

30 series airplanes to those listed in

Shorts Service Bulletin SD330–35–1,

dated February 25, 1999, and has

revised the Summary section of the AD

to refer to ‘‘certain,’’ rather than ‘‘all,’’

Model SD3–30 series airplanes.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the change

described previously. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

Cost Impact

The FAA estimates that 62 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 50

work hours per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Required parts will be provided by the

manufacturer at no cost to operators.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $186,000, or $3,000 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

Regulatory Impact

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 the following new airworthiness

directive:

2000–02–02 Short Brothers PLC:

Amendment 39–11520. Docket 99–NM–

223–AD.