Federal Register / Vol. 66, No. 116 / Friday, June 15, 2001 / Rules and Regulations 32531

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:

2001–12–10 Boeing: Amendment 39–12265.

Docket 2000–NM–303–AD.

Applicability: Model 777–200 series

airplanes, line numbers (L/N) 1 through 9

inclusive, 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 request approval for an

alternative method of compliance in

accordance with paragraph (c) 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 fracture of the inboard support

structure of the flaperon, which could result

in an in-flight loss of the inboard flaperon,

structural damage, and consequent reduced

controllability of the airplane, accomplish

the following:

Repetitive Inspections

(a) Before the accumulation of 4,000 total

flight cycles, or within 90 days after the

effective date of this AD, whichever occurs

later: Do a detailed visual and an ultrasonic

inspection of the lower flange of the flaperon

inboard support to find cracks, per Part 1 of

the Accomplishment Instructions of Boeing

Alert Service Bulletin 777–57A0036, dated

June 24, 1999.

(1) If no cracking is found: Repeat the

applicable inspections thereafter at intervals

not to exceed 300 flight cycles until

accomplishment of the terminating action

specified in paragraph (b) of this AD.

(2) If any cracking is found, before further

flight, do the terminating action required by

paragraph (b) of this AD, except, where the

service bulletin specifies to contact Boeing

for instructions, before further flight, repair

per a method approved by the Manager,

Seattle Aircraft Certification Office (ACO),

FAA; or per data meeting the type

certification basis of the airplane approved

by a Boeing Company Designated

Engineering Representative (DER) who has

been authorized by the Manager, Seattle

ACO, to make such findings. For a repair

method to be approved by the Manager,

Seattle ACO, as required by this paragraph,

the approval letter must specifically

reference this AD.

Terminating Action

(b) On or before the accumulation of 8,000

total flight cycles, or within 1,200 flight

cycles after the effective date of this AD,

whichever occurs later: Do the terminating

action (a high frequency eddy current

inspection to find cracks of the aft holes that

attach the failsafe strap to the lower flange,

oversizing of the holes if cracks are found,

and installation of a failsafe strap), per Part

2 of the Accomplishment Instructions of

Boeing Alert Service Bulletin 777–57A0036,

dated June 24, 1999. Accomplishment of this

paragraph terminates the repetitive

inspections required by paragraph (a) of this

AD.

Alternative Methods of Compliance

(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, 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 2: 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

(d) 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

(e) Except as provided by paragraph (a)(2)

of this AD, the actions shall be done in

accordance with Boeing Alert Service

Bulletin 777–57A0036, dated June 24, 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 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.

Effective Date

(f) This amendment becomes effective on

July 20, 2001.

Issued in Renton, Washington, on June 6,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–14725 Filed 6–14–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–116–AD; Amendment

39–12263; AD 2001–12–08]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 767 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 767

series airplanes, that requires removing

the two existing escape ropes in the

flight compartment; installing new

escape ropes, bags, and placards; and

replacing the nylon straps with new

straps; as applicable. This action is

necessary to ensure that flight crew

members safely reach the ground from

a flight compartment window in the

event of an emergency evacuation. This

action is intended to address the

identified unsafe condition.

32532 Federal Register / Vol. 66, No. 116 / Friday, June 15, 2001 / Rules and Regulations

DATES: Effective July 20, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 20,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle,

Washington 98124–2207. 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: Jim

Cashdollar, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2785; fax (425) 227–1181.

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 certain Boeing

Model 767 series airplanes was

published in the Federal Register on

January 16, 2001 (66 FR 3515). That

action proposed to require removing the

two existing escape ropes in the flight

compartment; installing new escape

ropes, bags, and placards; and replacing

the nylon straps with new straps; as

applicable.

Comments Received

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule.

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 as proposed.

Cost Impact

There are approximately 321 Model

767 series airplanes of the affected

design in the worldwide fleet. The FAA

estimates that 136 airplanes of U.S.

registry will be affected by this AD, that

it will take approximately 1 work hour

per airplane to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $4,718 per

airplane. Based on these figures, the cost

impact of the AD on U.S. operators is

estimated to be $649,808, or $4,778 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. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

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:

2001–12–08 Boeing: Amendment 39–12263.

Docket 2000–NM–116–AD.

Applicability: Model 767 series airplanes,

as listed in Boeing Alert Service Bulletin

767–25A0265, dated May 27, 1999;

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 request approval for an

alternative method of compliance in

accordance with paragraph (b) 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 ensure that flight crew members safely

reach the ground from a flight compartment

window in the event of an emergency

evacuation, accomplish the following:

Replacement

(a) Within 18 months after the effective

date of this AD, do the actions specified in

paragraphs (a)(1) and (a)(2) of this AD, as

applicable, per Boeing Alert Service Bulletin

767–25A0265, dated May 27, 1999.

(1) For all airplanes: Remove the two

existing escape ropes and install new escape

ropes, bags, and placards, as applicable, in

the flight compartment.

(2) For airplanes having serial numbers 1

through 107 inclusive; on which Boeing

Service Bulletin 767–25–0149, dated March

7, 1991 has been accomplished; or on which

neither Boeing Service Bulletin 767–25–

0149, dated March 7, 1991, nor 767–

25A0242, dated October 31, 1996, has been

accomplished: Replace the nylon straps with

new straps.

Alternative Methods of Compliance

(b) 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

Aircraft Certification Office (ACO), FAA.

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 2: 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

(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.

Federal Register / Vol. 66, No. 116 / Friday, June 15, 2001 / Rules and Regulations 32533

Incorporation by Reference

(d) The actions shall be done in accordance

with Boeing Alert Service Bulletin 767–

25A0265, dated May 27, 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 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.

Effective Date

(e) This amendment becomes effective on

July 20, 2001.

Issued in Renton, Washington, on June 6,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–14723 Filed 6–14–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NE–22–AD; Amendment

39–12261; AD 2001–12–06]

RIN 2120–AA64

Airworthiness Directives; General

Electric Company (GE) CF34–1A, –3A,

–3A1, –3A2, –3B, and –3B1 Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD), that is

applicable to GE CF34–1A, –3A, –3A1,

–3A2, –3B, and –3B1 turbofan engines

with No. 5 bearing rotating air seal part

number (P/N) 4019T60G01 installed.

This amendment requires initial and

repetitive checks of the magnetic chip

detector indicators, which are located in

the lubrication system for the engine

bearings, and installation of an

improved No. 5 bearing rotating air seal

as a terminating action. This

amendment is prompted by a report of

the failure of a No. 5 bearing rotating air

seal that led to a fire in the cavity of the

low pressure turbine (LPT),

overtemperature of the LPT turbine

disk, and excessive turbine disk growth.

The actions specified by this AD are

intended to prevent No.5 bearing

rotating air seal failures and possible

uncontained engine failures.

DATES: Effective date July 20, 2001.

ADDRESSES: Information regarding this

action may be examined at the Federal

Aviation Administration (FAA), New

England Region, Office of the Regional

Counsel, 12 New England Executive

Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT:

Eugene Triozzi, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone: (781) 238–7148,

fax: (781) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD that is applicable to GE

CF34–1A, –3A, –3A1, –3A2, –3B, and

–3B1 engines was published in the

Federal Register on February 27, 2001

(66 FR 12443). That action proposed to

require initial and repetitive checks of

magnetic chip detector indicators,

which are located in the lubrication

system for the engine bearings, in order

to detect No. 5 bearing roller distress

before air seal failure, and installation of

a new modified design No. 5 bearing

rotating air seal, P/N 4019T60G03, as

terminating action for the repetitive

inspection requirements of this AD.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Requests To Eliminate Repetitive

Inspection Requirements

Three commenters request that the

repetitive inspection requirements be

eliminated from the AD. The

commenters state that they are already

performing the inspections based upon

recommendations from the

manufacturer. The FAA does not agree.

Although these individual commenters

may already be complying with the

proposed requirements, the FAA has

determined that an unsafe condition

exists that warrants requiring all

operators to conduct mandatory

repetitive inspections, until the

terminating actions are accomplished.

Therefore, the FAA must issue an AD to

require repetitive inspections, regardless

of the manufacturer’s recommendations.

Requests To Change Compliance Time

for Initial Inspections

Two commenters request that the time

to comply with the initial inspection

requirements be increased from 30

hours after the effective date of the

proposed AD to 100 hours after the

effective date, for CF34–1A, –3A, and

–3A2 engines. The commenters feel that

a 100-hour initial inspection provides

an acceptable level of safety based on

risk analysis conducted by the type

certificate holder, and will reduce the

economic burden on operators. The

FAA agrees. Further review of risk

analysis data supports that an

acceptable level of safety would result

with a 100-hour initial inspection

threshold rather than a 30-hour initial

inspection threshold. Therefore, the

FAA has changed the initial inspection

compliance time for CF34–1A, –3A, and

–3A2 engines to ‘‘100 flight hours from

the effective date of this AD.’’

Requests To Change Compliance Time

for CF34–3B Repetitive Inspections

One commenter requests that the time

to comply with the repetitive inspection

requirements be increased from an

interval of 30 hours to an interval of 100

hours for CF34–3B engines. The

commenter states that the extended time

will reduce the economic impact on the

commenter due to additional

maintenance requirements, and make

the CF34–3B inspection requirements

the same as the CF34–3A inspection

requirements. The FAA does not agree.

Risk analysis data used by the FAA to

establish the AD requirements shows

that an unacceptable level of safety

would result from increasing the

inspection interval from 30 flight hours

to 100 flight hours for the CF34–3B

engine fleet.

Requests To Clarify Who May Perform

Maintenance Actions

One commenter requests that the

wording of the AD be revised to reflect

that the pilot may do the check, but a

maintenance technician must do any

required maintenance actions.

Additionally, the same commenter and

another commenter, request that the AD

be revised to clarify that on CF34–1A,

–3A, and –3A2 turbofan engines, chip

detector checks are maintenance actions

and are not to be performed by flight

crew. CF34–1A, –3A, and –3A2 turbofan

engine models have individual chip

detectors. Those chip detectors are

checked with an ohmmeter, unlike the

CF34–3A1, –3B, and –3B1 engine

models, which have a single master chip

detector with a white triangle or

illuminated indicator. The FAA agrees.

The intent of the AD is to allow chip

detector indicator checks to be done by

the pilot for engine models with the

master chip detector installation.

Although the proposed AD would not

have authorized the pilot to do any task

beyond a visual check of the indicator,

the FAA agrees that additional clarity is

needed. Therefore, the FAA has revised