Federal Register / Vol. 65, No. 51 / Wednesday, March 15, 2000 / Rules and Regulations 13875

Optional Visual Inspection

(d) The actions required by paragraphs (a),

(b), and (c) of this AD may be accomplished

at the time specified in paragraph (d)(1) of

this AD, provided that the action specified in

paragraph (d)(2) is accomplished.

(1) Within 1 year or 4,500 flight cycles after

the effective date of this AD, whichever

occurs later, accomplish the actions specified

in paragraph (a), (b), or (c) of this AD, as

applicable; and

(2) Within 200 days or 1,500 flight cycles

after the effective date of this AD, whichever

occurs later, perform a detailed visual

inspection to detect fretting or corrosion of

the axle flange bolt holes. If any fretting or

corrosion is detected, prior to further flight,

accomplish the repair procedures specified

in the ‘‘Recommended Operator Action’’

section of Boeing AOT M–7272–96–1442,

dated March 29, 1996.

Note 3: For the purposes of this AD, a

detailed inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

Alternative Methods of Compliance

(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, Seattle

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Seattle ACO.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permits

(f) Special flight permits may be issued in

accordance with §§ 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

(g) Except as provided by paragraphs (a)(1),

(b)(1), and (c)(1) of this AD, the actions shall

be done in accordance with Boeing All

Operators Telex (AOT) M–7272–96–1442,

dated March 29, 1996; AlliedSignal Service

Bulletin 2601042–32–003, dated March 15,

1997; and Boeing Service Bulletin 737–32–

1253, dated November 7, 1991; as applicable.

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 Airplane Group,

P.O. Box 3707, Seattle, Washington 98124–

2207. 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.

(h) This amendment becomes effective on

April 19, 2000.

Issued in Renton, Washington, on March 6,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–5890 Filed 3–14–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–SW–85–AD; Amendment

39–11627; AD 2000–05–17]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France Model EC 120B Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to Eurocopter France Model

EC 120B helicopters, that currently

requires, at specified time intervals,

inspecting the engine coupling tube for

cracks and replacing any cracked engine

coupling tube with an airworthy engine

coupling tube. This amendment

requires, at specified time intervals,

visually inspecting and dye-penetrant

inspecting the coupling tube for any

crack and replacing any cracked

coupling tube with a reinforced,

airworthy coupling tube. Replacing all

coupling tubes and certain engine

support fitting components is required

on or before March 31, 2000. This

amendment is prompted by the

discovery of cracks in several coupling

tubes. The actions specified by this AD

are intended to prevent coupling failure,

loss of engine drive, and a subsequent

forced landing.

DATES: Effective March 27, 2000. The

incorporation by reference of certain

publications listed in the regulations is

approved by the Director of the Federal

Register as of March 27, 2000.

Comments for inclusion in the Rules

Docket must be received on or before

May 15, 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–85–

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 the

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.

FOR FURTHER INFORMATION CONTACT:

Shep Blackman, Aerospace Engineer,

Regulations Group, Rotorcraft

Directorate, FAA, 2601 Meacham Blvd.,

Fort Worth, Texas 76137, telephone

(817) 222–5296, fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: On

September 2, 1999, the FAA issued

Emergency Priority Letter AD 99–19–23

and on September 22, 1999, issued the

final rule; request for comments for AD

99–19–23, Amendment 39–11343 (64

FR 53623, October 4, 1999), to require

within 10 hours time-in-service (TIS),

and thereafter, at intervals not to exceed

10 hours TIS, inspecting a specified

engine coupling tube for cracks and

replacing any cracked engine coupling

tube with an airworthy engine coupling

tube. That action was prompted by the

discovery, during routine maintenance

inspections, of three cracked engine

coupling tubes caused by structural

resonance. That condition, if not

corrected, could result in coupling

failure, loss of engine drive, and a

subsequent forced landing.

Since the issuance of that AD, the

manufacturer has issued Eurocopter

Service Bulletin No. 05–001, dated

September 23, 1999, which introduces a

new alternative check procedure. The

Direction Generale de L’Aviation Civile

(DGAC), which is the airworthiness

authority for France, classified this

service bulletin as mandatory and

issued AD 1999–349–002(A) R2, dated

November 3, 1999, to ensure the

continued airworthiness of these

helicopters in France. The manufacturer

has also issued Eurocopter Service

Bulletin No. 63–001, dated November

10, 1999, which recommends installing

a reinforced coupling tube and

disassembling the engine mount fitting

assembly. The manufacturer then issued

Eurocopter Service Bulletin No. 01–002,

dated December 23, 1999, which

declares that coupling tubes, P/N

C631A1002101, and certain engine

support fitting components are unfit for

flight after March 31, 2000. The DGAC

classified this service bulletin as

mandatory and issued AD 2000–058–

13876 Federal Register / Vol. 65, No. 51 / Wednesday, March 15, 2000 / Rules and Regulations

003(A), dated February 9, 2000, to

ensure the continued airworthiness of

these helicopters in France.

This helicopter model is

manufactured in France 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 DGAC has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the DGAC,

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 an unsafe condition has been

identified that is likely to exist or

develop on other Eurocopter France

Model EC 120B helicopters of the same

type design, this AD supersedes AD 99–

19–23 to require periodic visual and

dye-penetrant inspections on each

coupling tube, replacement of any

cracked coupling tube, and replacement

of the coupling tube and certain engine

mount fitting components on or before

March 31, 2000. The actions must be

accomplished in accordance with the

service bulletins 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, the actions

stated previously must be accomplished

at the specified time intervals, 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 12 helicopters

will be affected by this proposed AD,

that it will take approximately 1 work

hour to visually inspect each coupling

tube and 6.5 work hours to dyepenetrant inspect each coupling tube.

Replacing each coupling tube and

installing the engine mount fitting

components will take approximately 12

work hours per helicopter. The average

labor rate is $60. The manufacturer

states that they will provide the

components necessary for replacing the

coupling tubes free of charge. Based on

these figures and the manufacturer’s

representation that it will provide the

repair parts free of charge, the total cost

impact of the AD on U.S. operators is

estimated to be $19,400, assuming 2

visual inspections, 2 dye-penetrant

inspections, 1 coupling tube

replacement, and 1 installation of the

engine support fitting components on

each helicopter.

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–85–09AD.’’ 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 final rule 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

removing Amendment 39–11343 (64 FR

53623, October 4, 1999), and by adding

a new airworthiness directive (AD),

Amendment 39–11627, to read as

follows:

AD 2000–05–17 Eurocopter France:

Amendment 39–11627. Docket No. 99–

SW–85–AD. Supersedes AD 99–19–23,

Amendment 39–11343, Docket No. 99–

SW–53–AD.

Applicability: Model EC 120B helicopters

with engine coupling tube (coupling tube),

part number (P/N) C631A1002101, 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 (e) 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 coupling failure, loss of engine

drive, and a subsequent forced landing,

accomplish the following:

Federal Register / Vol. 65, No. 51 / Wednesday, March 15, 2000 / Rules and Regulations 13877

(a) Within 10 hours time-in-service (TIS),

and thereafter at intervals not to exceed 10

hours TIS except when required to perform

the inspection required by paragraph (b) of

this AD while each coupling tube, P/N

C631A1002101, is installed, inspect for any

crack in accordance with the

Accomplishment Instructions, paragraph

2.B.1., of Eurocopter Service Bulletin No. 05–

001, dated September 23, 1999 (SB 05–001).

(b) Within 10 hours TIS, and thereafter at

intervals not to exceed 30 hours TIS, after

each coupling tube, P/N C631A1002101, has

been removed, inspect for any crack in

accordance with paragraph 2.B.2. of SB 05–

001.

Note 2: Operators are not required to

inform the manufacturer when a crack is

found.

(c) When a crack is found as a result of the

inspections conducted in accordance with

either paragraph (a) or (b) of this AD, or by

March 31, 2000, whichever occurs first,

replace the coupling tube with a reinforced,

airworthy coupling tube, P/N C631A1101101,

and replace the engine mount fittings in

accordance with Eurocopter Service Bulletin

No. SB 63–001, dated November 10, 1999,

using new, airworthy, engine mount fitting

components to replace the following:

• Teflon spacer, P/N C714A1010208;

• Black-colored spring washers, 10.2 x 28

Type-C;

• Blue-colored hinge yoke, P/N

C714A1010212; and

• Special washer, P/N C714A1010213.

Note 3: Eurocopter Service Bulletin No.

01–002 pertains to unairworthiness of the

four engine mount fitting components listed

in paragraph (c) of this AD.

(d) Installing the reinforced, airworthy

coupling tubes, P/N C631A1101101, and

replacing the engine mount fitting

components using new, airworthy, engine

mount fitting components, as specified in

paragraph (c) of this AD, constitutes

terminating action for the requirements of

this AD.

(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, 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 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Regulations Group.

(f) Special flight permits may be issued in

accordance with §§ 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.

(g) The inspections and modifications shall

be done in accordance with the

Accomplishment Instructions, paragraph

2.B.1., of Eurocopter Service Bulletin No. 05–

001, dated September 23, 1999; Eurocopter

Service Bulletin No. 63–001, dated November

10, 1999; and Eurocopter Service Bulletin

No. 01–002, dated December 23, 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, 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.

(h) This amendment becomes effective on

March 27, 2000.

Note 5: The subject of this AD is addressed

in Direction Generale de L’Aviation Civile

(France) AD 1999–349–002(A) R2, dated

November 3, 1999 and AD 2000–058–003(A),

dated February 9, 2000.

Issued in Fort Worth, Texas, on March 6,

2000.

Henry A. Armstrong,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 00–6034 Filed 3–14–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–SW–61–AD; Amendment

39–11626; AD 2000–05–16]

RIN 2120–AA64

Airworthiness Directives; Sikorsky

Model S–61 Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD)

applicable to Sikorsky Model S–61

helicopters. This action requires

inspecting certain pylon upper and

lower hinge web fittings (web fittings)

for corrosion or a crack and either

repairing certain web fittings or

replacing any unairworthy web fittings

with airworthy web fittings. The AD

also requires creating a log card or

equivalent record and implementing a

recurring inspection of the web fittings.

This amendment is prompted by the

discovery of extensive cracking in the

area of the web fittings. The actions

specified in this AD are intended to

prevent structural failure of the tail

boom due to a crack or corrosion of

certain web fittings and subsequent loss

of control of the helicopter.

DATES: Effective March 30, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 30,

2000.

Comments for inclusion in the Rules

Docket must be received on or before

May 15, 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–61–

AD, 2601 Meacham Blvd., Room 663,

Fort Worth, Texas 76137.

The service information referenced in

this AD may be obtained from Sikorsky

Aircraft Corporation, Attn: Manager,

Commercial Tech Support, 6900 Main

Street, P. O. Box 9729, Stratford,

Connecticut 06497–9129, phone (203)

386–7860, fax (203) 386–4703. This

information may be examined at the

FAA, Office of the 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.

FOR FURTHER INFORMATION CONTACT:

Brian K. Murphy, Aerospace Engineer,

ANE–150, 12 New England Executive

Park, Burlington, MA 01803, telephone

(781) 238–7739, fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: This

amendment adopts a new AD applicable

to Sikorsky Model S–61 helicopters

with pylon, part number, (P/N) S6120–

76265–001 or S6120–76266–507,

installed. The AD requires inspecting

and repairing or, if necessary, replacing

certain web fittings and the fitting

faying surfaces. The AD also requires

making an entry on the log card or

equivalent record.

This amendment is prompted by the

discovery of extensive cracking in the

area of the web fitting. The actions

specified in this AD are intended to

prevent structural failure of certain web

fittings due to stress corrosion and

subsequent structural failure of the

tailboom. This condition, if not

corrected, could result in loss of control

of the helicopter.

The FAA has reviewed Sikorsky

Aircraft Corporation Alert Service

Bulletin No. 61B20–33, dated

September 3, 1999 (ASB), which

describes procedures for inspecting and

repairing or, if necessary, replacing

certain web fittings having a crack or

corrosion.

Since an unsafe condition has been

identified that is likely to exist or

develop on other Sikorsky Model S61

helicopters of the same type design, this

AD is being issued to prevent structural

failure of certain web fittings due to a

crack or corrosion. This AD requires