31256 Federal Register / Vol. 65, No. 96 / Wednesday, May 17, 2000 / Rules and Regulations

AD 2000–10–07 Eurocopter Deutschland

GMBH: Amendment 39–11731. Docket

No. 99–SW–05–AD.

Applicability: Model EC 135 helicopters,

serial numbers 0005 through 0071,

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 within 50 hours

time-in-service, unless accomplished

previously.

To prevent failure of an oil cooler fan

splined drive shaft (shaft), loss of oil cooling,

and a subsequent engine shutdown during

flight, accomplish the following:

(a) Replace each shaft, part number (P/N)

L 792M3004 225, with an airworthy shaft, P/

N L 792M3004 235.

(b) Re-identify the P/N on each oil cooler

fan (fan) using a rubber stamp or smudgeproof paint or equivalent as follows:

(1) On the left fan, change the P/N from L

792M3004 102 to L 792M3004 103.

(2) On the right fan, change the P/N from

L 792M3005 102 to L 792M3005 103.

(c) Change the P/N on the gearbox

component history card or equivalent record

to reflect the revised part numbers.

Note 2: Eurocopter Alert Service Bulletin

No. EC 135–79A–001, dated January 23,

1998, pertains to the subject of this AD.

(d) Replacing the shaft, re-identifying the

fans, and recording this on the gearbox

component history card or equivalent record

constitute terminating actions 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 3: 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) This amendment becomes effective on

June 21, 2000.

Note 4: The subject of this AD is addressed

in Luftfahrt-Bundesamt (Federal Republic of

Germany) AD No. 1998–109, dated February

26, 1998.

Issued in Fort Worth, Texas, on May 9,

2000.

Henry A. Armstrong,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 00–12356 Filed 5–16–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–SW–34–AD; Amendment

39–11732; AD 2000–10–08]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France Model SA–365N1, AS–365N2,

and SA–366G1 Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to Eurocopter France Model SA–

365N1, AS–365N2, and SA–366G1

helicopters and requires conducting

inspections of each tail rotor blade for

bonding separation, measuring the

clearance between the tip of each tail

rotor blade and the circumference of the

air duct, and replacing the blade if

necessary. This amendment is prompted

by an inflight incident in which the tail

rotor blades were significantly damaged

due to bonding separation. The actions

specified by this AD are intended to

prevent damage to a tail rotor blade, loss

of tail rotor control, and subsequent loss

of control of the helicopter.

EFFECTIVE DATE: June 21, 2000.

FOR FURTHER INFORMATION CONTACT:

Sharon Miles, Aviation Safety Engineer,

FAA, Rotorcraft Directorate, Regulations

Group, Fort Worth, Texas 76193–0111,

telephone (817) 222–5122, fax (817)

222–5961.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD for Eurocopter France

Model SA–365N1, AS–365N2, and SA–

366G1 helicopters was published in the

Federal Register on February 29, 2000

(65 FR 10724). That action proposed to

require conducting inspections of each

tail rotor blade for bonding separation,

measuring the clearance between the tip

of each tail rotor blade and the

circumference of the air duct, and

replacing the blade if necessary.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed.

The FAA estimates that 136

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 1 work hour per

helicopter to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $1,000 per

helicopter. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $144,160.

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 FAA, Office of the

Regional Counsel, Southwest Region,

2601 Meacham Blvd., Room 663, Fort

Worth, Texas.

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.

Federal Register / Vol. 65, No. 96 / Wednesday, May 17, 2000 / Rules and Regulations 31257

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive to

read as follows:

AD 2000–10–08 Eurocopter France:

Amendment 39–11732. Docket No. 99–

SW–34–AD.

Applicability: Model SA–365N1, AS–

365N2, and SA–366G1 helicopters, with a

tail rotor blade, part number (P/N) 365A33–

2131, 365A12–0010, or 365A12–0020, all

dash numbers, 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 (f) 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 damage to a tail rotor blade

(blade), loss of tail rotor control, and

subsequent loss of control of the helicopter:

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

and thereafter prior to the first flight of each

day, conduct the following visual inspection

of each blade (see Figure 1):

(1) Zone A: If a blister is detected on the

blade suction face, conduct a tapping test

inspection on the whole blade for bonding

separation. If bonding separation or a crack

is found, replace the blade with an airworthy

blade before further flight.

(2) Zone B: If a crack, wrinkling, or a blister

is found, replace the blade with an airworthy

blade before further flight.

(b) Within 10 hours TIS, conduct a tapping

test inspection on each blade. If there is

bonding separation, replace the blade with an

airworthy blade before further flight.

Note 2: Revisions 5 of Eurocopter France

Service Bulletins 05.09 and 05.00.17, both

dated December 18, 1998, pertain to the

subject of this AD.

(c) Thereafter, at intervals not to exceed 25

hours TIS or every 50 cycles (each takeoff

and landing equals 1 cycle), whichever

occurs first, conduct a tapping test inspection

for bonding separation on all blades with a

serial number (S/N) less than 18912, and

blades, P/N 365A12–0020–00 or 365A12–

0020–01, with a S/N equal to or greater than

18912. If bonding separation or a crack is

found, replace the blade with an airworthy

blade before further flight.

(d) Thereafter, at intervals not to exceed

100 hours TIS or 200 cycles, whichever

occurs first, conduct a tapping test inspection

for bonding separation on blades, P/N

365A12–0020–02 or 365A12–0020–03. If

bonding separation or a crack is found,

replace the blade with an airworthy blade

before further flight.

(e) Within 10 hours TIS, and thereafter at

intervals not to exceed 100 hours TIS or 200

cycles, whichever occurs first, measure the

blade-to-air duct clearance. If the clearance is

less than 3 mm, replace the blade with an

airworthy blade before further flight.

BILLING CODE 4910–13–U

31258 Federal Register / Vol. 65, No. 96 / Wednesday, May 17, 2000 / Rules and Regulations

BILLING CODE 4910–13–C

Federal Register / Vol. 65, No. 96 / Wednesday, May 17, 2000 / Rules and Regulations 31259

(f) 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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Regulations Group.

(g) 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.

(h) This amendment becomes effective on

June 21, 2000.

Note 4: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

AD’s 88–152–010(A)R5 and 88–153–

023(A)R5, both dated December 30, 1998.

Issued in Fort Worth, Texas, on May 9,

2000.

Henry A. Armstrong,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 00–12354 Filed 5–16–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–04–AD; Amendment

39–11730; AD 2000–10–06]

RIN 2120–AA64

Airworthiness Directives; MD

Helicopters Inc. Model MD900

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) for

MD Helicopters Inc. (MDHI) Model

MD900 helicopters. This action requires

visually inspecting the drive shaft to

determine the assembly part number

(P/N) and marking the drive shaft

assembly P/N and serial number (S/N)

on any unmarked drive shaft. This AD

also requires creating a component

history card or equivalent record for

certain drive shaft assemblies and

replacing any drive shaft assembly that

has reached its life limit. This

amendment is prompted by the

discovery of several drive shafts with no

assembly P/N marked on the part,

which could result in a drive shaft

remaining in service past its life limit.

The actions specified in this AD are

intended to prevent failure of the drive

shaft due to fatigue, which could result

in total loss of drive to the main rotor

hub and subsequent loss of control of

the helicopter.

DATES: Effective June 1, 2000.

Comments for inclusion in the Rules

Docket must be received on or before

July 17, 2000.

ADDRESSES: Submit comments by mail

in triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 2000–SW–

04–AD, 2601 Meacham Blvd., Room

663, Fort Worth, Texas 76137. You may

also send comments electronically to

the Rules Docket at the following

address: 9–asw–adcomments@faa.gov.

FOR FURTHER INFORMATION CONTACT:

Elizabeth Bumann, Aviation Safety

Engineer, FAA, Los Angeles Aircraft

Certification Office, Propulsion Branch,

3960 Paramount Blvd., Lakewood,

California 90712–4137, telephone (562)

627–5265, fax (562) 627–5210.

SUPPLEMENTARY INFORMATION: This

amendment adopts a new AD for MDHI

Model MD900 helicopters. On February

19, 1999, the FAA issued AD 99–05–08,

Amendment 39–11056 (64 FR 10209,

March 3, 1999), for MDHI Model MD900

helicopters to establish or reduce life

limits for various parts, including the

drive shaft assembly. That AD was

prompted by analysis that indicated a

need for establishing or reducing life

limits to avoid fatigue failure of certain

parts. Since issuance of that AD, several

drive shaft assemblies were found

without a P/N marked on the drive

shafts. This could result in the drive

shaft remaining in service past its life

limit since operators may mistakenly

use the subassembly P/N for

determining whether the life limit listed

in AD 99–05–08 applies. A drive shaft

in operation past its life limit could fail

due to fatigue. This condition, if not

corrected, could result in total loss of

drive to the main rotor hub and

subsequent loss of control of the

helicopter.

The FAA has reviewed MDHI Service

Bulletin (SB) SB900–062 R1, dated

December 16, 1999, which describes

procedures for visually inspecting the

drive shaft to determine the assembly

P/N and marking the drive shaft

assembly P/N and serial number (S/N)

on any unmarked drive shaft. The SB

also specifies creating component

history cards for certain drive shaft

assemblies, verifying the life limit, and

replacing the drive shaft assembly, if

necessary.

Since an unsafe condition has been

identified that is likely to exist or

develop on other MDHI Model MD900

helicopters of the same type design, this

AD is being issued to prevent failure of

the drive shaft. This AD requires

visually inspecting the drive shaft to

determine the assembly P/N and

marking the drive shaft assembly P/N

and S/N on any unmarked drive shaft.

This AD also requires creating

component history cards for certain

drive shaft assemblies and replacing the

drive shaft assembly if the drive shaft

assembly has reached its life limit. The

short compliance time involved is

required because the previously

described critical unsafe condition can

adversely affect controllability of the

helicopter. Therefore, the actions of this

AD are required prior to accumulating

1,450 hours time-in-service (TIS) on the

drive shaft or before further flight if TIS

equals or exceeds 1,450 hours, 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 this AD will

affect 28 helicopters, that it will take

approximately 2 work hours to

accomplish the required actions, and

that the average labor rate is $60 per

work hour. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $3,360.

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