Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations 37011

(2) Piece-part exposure is defined as

disassembly and removal of the stage 14 disk

from the HPC rotor structure, regardless of

any blades, locking lugs, bolts or balance

weights assembled to the disk.

(3) An engine shop visit is defined as the

introduction of an engine into a shop when

a major engine flange is separated. The

following maintenance actions are not

considered engine shop visits for the purpose

of this AD:

(i) Introduction of an engine into a shop

solely for removal or replacement of the

Stage 1 Fan Disk;

(ii) Introduction of an engine into a shop

solely for replacement of the Turbine Rear

Frame;

(iii) Introduction of an engine into a shop

solely for replacement of the Accessory

Gearbox or Transfer Gearboxes;

(iv) Introduction of an engine into a shop

solely for replacement of the Fan Forward

Case.

(v) Introduction of an engine into a shop

for any combination of exceptions specified

in paragraphs (i)(3)(i) through (i)(3)(iv);

Alternative Methods of Compliance

(j) 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, Engine

Certification Office. Operators shall submit

their request through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

Incorporation by Reference

(k) The inspections shall be done in

accordance with paragraphs 2.A. through 2.B.

of GE CF6–50 ASB No. 72–A1144, dated

March 19, 1998, or ASB No. 72–A1144,

Revision 1, dated May 13, 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 General

Electric Company via Lockheed Martin

Technology Services, 10525 Chester Road,

Suite C, Cincinnati, Ohio 45215, telephone

(513) 672–8400, fax (513) 672–8422. Copies

may be inspected at the FAA, New England

Region, Office of the Regional Counsel, 12

New England Executive Park, Burlington,

MA; or at the Office of the Federal Register,

800 North Capitol Street, NW, suite 700,

Washington, DC.

Special Flight Permit

(l) 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 aircraft to a

location where the requirements of this AD

can be accomplished.

Effective Date of This AD

(m) This amendment becomes effective on

August 14, 2000.

Issued in Burlington, Massachusetts, on

May 25, 2000.

Thomas A. Boudreau,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 00–14017 Filed 6–12–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–138–AD; Amendment

39–11770; AD 2000–10–51]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 767 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This document publishes in

the Federal Register an amendment

adopting airworthiness directive (AD)

2000–10–51 that was sent previously to

all known U.S. owners and operators of

certain Boeing Model 767 series

airplanes by individual notices. This AD

requires a one-time inspection to

determine whether certain bolts are

installed in the side load underwing

fittings on both struts, and various

follow-on actions, if necessary. This

action is prompted by a report that two

fractured bolts and one cracked bolt

were found in the side load underwing

fittings. The actions specified by this

AD are intended to detect and correct

cracking or fracturing of the tension

bolts on the side load underwing fittings

on the strut, which would eventually

result in loss of the strut.

DATES: Effective June 19, 2000, to all

persons except those persons to whom

it was made immediately effective by

emergency AD 2000–10–51, issued May

18, 2000, which contained the

requirements of this amendment.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 19,

2000.

Comments for inclusion in the Rules

Docket must be received on or before

August 14, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

138–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The applicable service information

may be obtained from Boeing

Commercial Airplane Group, P.O. Box

3707, Seattle, Washington 98124–2207.

This information may be examined 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.

FOR FURTHER INFORMATION CONTACT:

James Rehrl, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Transport Airplane Directorate, Seattle

Aircraft Certification Office, 1601 Lind

Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2783;

fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: On May

18, 2000, the FAA issued emergency AD

2000–10–51, which is applicable to

certain Boeing Model 767 series

airplanes.

On May 15, 2000, the FAA received

a report indicating that an operator

found two fractured bolts and one

cracked bolt in the side load underwing

fittings of a Model 767–200 series

airplane. On the affected airplane, both

tension bolts on the outboard side load

underwing fitting were completely

fractured, and one bolt on the inboard

side load underwing fitting was cracked.

The affected airplane had accumulated

65,759 total flight hours and 17,021 total

flight cycles. The cracking and

fracturing of the tension bolts is due to

stress corrosion. The tension bolts are

made of H–11 steel material, which

service history has shown to be

susceptible to stress corrosion. Fracture

of the tension bolts in the side load

underwing fittings, if not corrected,

would eventually result in loss of the

strut.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Alert Service Bulletin 767–

57A0074, dated May 17, 2000, and

Revision 1, dated May 18, 2000, which

describes procedures for a one-time

inspection to determine whether H–11

steel tension bolts are installed in the

side load underwing fittings on both

struts. If any H–11 bolts are found, or if

the type of bolt cannot be determined,

the alert service bulletin also describes

procedures for repetitive ultrasonic

inspections to detect cracking or

fracturing of the tension bolts in the side

load underwing fittings on both struts,

and corrective action, if necessary.

Corrective action involves replacement

of both tension bolts in the affected side

load underwing fitting with new,

improved bolts. The new, improved

37012 Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations

bolts are made of Inconel, which is more

resistant to stress corrosion cracking

than H–11 steel. Replacement of all H–

11 steel tension bolts in the side load

underwing fittings with new, improved

bolts, as described in the alert service

bulletin, eliminates the need for the

repetitive inspections.

Explanation of Applicability

This AD applies to Model 767 series

airplanes having line numbers 1 through

230 inclusive. The airplane

manufacturer’s records show that

airplanes having line numbers 1 through

162 inclusive are likely to have H–11

steel tension bolts installed in the side

load underwing fittings on the struts.

However, the FAA has determined that

it is possible that airplanes with line

numbers 163 through 230 inclusive also

have H–11 steel bolts installed.

Therefore, this AD requires a one-time

inspection on all Model 767 series

airplanes with line numbers 1 through

230 inclusive to determine whether H–

11 steel tension bolts are installed. For

airplanes having line numbers 1 through

162 inclusive, this AD requires the

initial inspection within 5 days. For

airplanes having line numbers 163

through 230 inclusive, this AD requires

the initial inspection within 10 days.

Also, for airplanes having line numbers

163 through 230 inclusive on which H–

11 steel bolts are found to be installed,

this AD requires that operators report

this fact to the FAA.

Explanation of Requirements of the

Rule

Since the unsafe condition described

is likely to exist or develop on other

airplanes of the same type design, the

FAA issued emergency AD 2000–10–51

to require a one-time inspection to

determine whether H–11 steel tension

bolts are installed in the side load

underwing fittings on both struts. If an

H–11 steel tension bolt is installed, or

if the type of bolt cannot be determined,

this AD requires repetitive ultrasonic

inspections to detect cracking or

fracturing of the tension bolts in the side

load underwing fittings on both struts,

and corrective action, if necessary. For

certain airplanes, this AD also requires

additional inspections to detect

discrepancies of adjacent structure. For

certain other airplanes, as described

previously, this AD requires that

operators report results of inspection

findings to the FAA. This AD also

provides an optional terminating action

for the repetitive inspections described

previously. The actions are required to

be accomplished in accordance with the

alert service bulletin described

previously, except as discussed below.

Difference Between Alert Service

Bulletin and This AD

Operators should note that the alert

service bulletin recommends that the

one-time inspection to determine

whether H–11 steel tension bolts are

installed be performed within 5 days

after receipt of the alert service bulletin.

However, as described previously, this

AD requires that the inspection be

accomplished within 5 days after the

effective date of this AD only on

airplanes having line numbers 1 through

162 inclusive. On airplanes having line

numbers 163 through 230 inclusive, this

AD requires that this inspection be

accomplished within 10 days.

Operators also should note that the

alert service bulletin specifies that, if

both tension bolts on one fitting are

found cracked or fractured, the

manufacturer must be contacted for

additional inspection requirements to

detect discrepancies of adjacent

structure. This AD requires such

additional inspection requirements to be

accomplished in accordance with a

method approved by the FAA.

Interim Action

This is considered to be interim

action. The FAA is currently

considering requiring the replacement

of all H–11 steel tension bolts in the

side load underwing fittings with new,

improved bolts, which would constitute

terminating action for the repetitive

inspections required by this AD.

However, the planned compliance time

for the replacement would be

sufficiently long so that notice and

opportunity for prior public comment

would be practicable.

Determination of Rule’s Effective Date

Since it was found that immediate

corrective action was required, notice

and opportunity for prior public

comment thereon were impracticable

and contrary to the public interest, and

good cause existed to make the AD

effective immediately by individual

notices issued on May 18, 2000, to all

known U.S. owners and operators of

Boeing Model 767 series airplanes

having line numbers 1 through 230

inclusive. These conditions still exist,

and the AD is hereby published in the

Federal Register as an amendment to

section 39.13 of the Federal Aviation

Regulations (14 CFR 39.13) to make it

effective to all persons.

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 shall 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 Number 2000–NM–138–AD.’’

The postcard will be date stamped and

returned to the commenter.

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.

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.

Federal Register / Vol. 65, No. 114 / Tuesday, June 13, 2000 / Rules and Regulations 37013

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 the following new airworthiness

directive:

2000–10–51 Boeing: Amendment 39–11770.

Docket 2000–NM–138–AD.

Applicability: Model 767 series airplanes,

line numbers (L/N) 1 through 230 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 (g) 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 detect and correct cracking or fracturing

of the tension bolts on the side load

underwing fittings on the strut, which would

eventually result in loss of the strut,

accomplish the following:

One-Time Inspection

(a) At the applicable time specified in

paragraph (a)(1) or (a)(2) of this AD, perform

a one-time inspection of the tension bolts in

the side load underwing fittings on both

struts to determine whether tension bolts

made of H–11 steel are installed, in

accordance with Boeing Alert Service

Bulletin 767–57A0074, dated May 17, 2000,

or Revision 1, dated May 18, 2000. If the

inspection shows conclusively that no H–11

steel bolt is installed, no further action is

required by this AD.

(1) For airplanes having L/N 1 through 162

inclusive: Inspect within 5 days after the

effective date of this AD.

(2) For airplanes having L/N 163 through

230 inclusive: Inspect within 10 days after

the effective date of this AD.

Repetitive Inspections

(b) If any H–11 steel bolt is found during

the inspection required by paragraph (a) of

this AD, or if the type of bolt cannot be

determined: Prior to further flight, perform

an ultrasonic inspection to detect cracking or

fracturing of the tension bolts in the side load

underwing fittings on both struts, in

accordance with Boeing Alert Service

Bulletin 767–57A0074, dated May 17, 2000,

or Revision 1, dated May 18, 2000. Repeat the

inspection thereafter at intervals not to

exceed 500 flight hours or 300 flight cycles,

whichever occurs later.

Replacement

(c) If any cracked or fractured bolt is found

during any inspection required by paragraph

(b) of this AD, prior to further flight, replace

both tension bolts in the affected side load

underwing fitting with new, improved bolts,

in accordance with Boeing Alert Service

Bulletin 767–57A0074, dated May 17, 2000,

or Revision 1, dated May 18, 2000.

Additional Inspection Requirements

(d) If both tension bolts in one side load

underwing fitting are found cracked or

fractured during any inspection required by

paragraph (b) of this AD, prior to further

flight, perform inspections to detect

discrepancies of adjacent structure in

accordance with a method approved by the

Manager, Seattle Aircraft Certification Office

(ACO), FAA, Transport Airplane Directorate.

For an inspection method to be approved by

the Manager, Seattle ACO, as required by this

paragraph, the Manager’s approval letter

must specifically reference this AD.

Reporting Requirement

(e) For airplanes having L/N 163 through

230 inclusive on which an H–11 bolt is found

installed, or on which the type of bolt cannot

be determined during the inspection required

by paragraph (a) of this AD: Within 48 hours

after performing the inspection required by

paragraph (b) of this AD, submit a report of

findings to the Manager, Seattle ACO, FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington 98055–

4056; fax (425) 227–1181. The report must

include the type of bolt found and the

airplane serial number. Information

collection requirements contained in this

regulation have been approved by the Office

of Management and Budget (OMB) under the

provisions of the Paperwork Reduction Act of

1980 (44 U.S.C. 3501 et seq.), and have been

assigned OMB Control Number 2120–0056.

Optional Terminating Action

(f) Replacement of all H–11 steel tension

bolts in the side load underwing fittings on

both struts with new, improved bolts, in

accordance with Boeing Alert Service

Bulletin 767–57A0074, dated May 17, 2000,

or Revision 1, dated May 18, 2000,

constitutes terminating action for this AD.

Alternative Methods of Compliance

(g) 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

(h) 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

(i) Except as provided by paragraph (d) of

this AD, the actions shall be done in

accordance with Boeing Alert Service

Bulletin 767–57A0074, dated May 17, 2000,

or Boeing Alert Service Bulletin 767–

57A0074, Revision 1, dated May 18, 2000.

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

(j) This amendment becomes effective on

June 19, 2000, to all persons except those

persons to whom it was made immediately

effective by emergency AD 2000–10–51,

issued on May 18, 2000, which contained the

requirements of this amendment.

Issued in Renton, Washington, on June 1,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–14314 Filed 6–12–00; 8:45 am]

BILLING CODE 4910–13–U