Federal Register / Vol. 66, No. 112 / Monday, June 11, 2001 / Rules and Regulations 31141

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

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 5: 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 §§ 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) The actions shall be done in accordance

with Boeing Alert Service Bulletin 737–

29A1073, Revision 3, dated December 2,

1999; Boeing Alert Service Bulletin 737–

29A1081, dated December 2, 1999: Boeing

Alert Service Bulletin 757–29A0048,

Revision 3, dated December 2, 1999; Boeing

Alert Service Bulletin 757–29A0051, dated

December 2, 1999; Boeing Service Bulletin

767–29A0083, Revision 4, dated September

28, 2000; Boeing Alert Service Bulletin 737–

29A1078, dated December 7, 2000; Boeing

Alert Service Bulletin 737–29A1082, dated

December 7, 2000; Boeing Alert Service

Bulletin 757–29A0049, dated December 7,

2000; Boeing Alert Service Bulletin 757–

29A0052, dated December 7, 2000; or Boeing

Alert Service Bulletin 767–29A0090, dated

December 7, 2000; 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.

Effective Date

(f) This amendment becomes effective on

July 16, 2001.

Issued in Renton, Washington, on May 25,

2001.

Vi L. Lipski,

Manager, Transport Airplane

Directorate,Aircraft Certification Service.

[FR Doc. 01–14000 Filed 6–8–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–126–AD; Amendment

39–12251; AD 2001–09–51]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 737–600, –700, –700C, and –800

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)

2001–09–51 that was sent previously to

all known U.S. owners and operators of

Boeing Model 737–600, –700, –700C,

and –800 series airplanes by individual

notices. This AD requires inspection of

the small jam nut on the elevator tab

control rods to detect inspection putty

and to determine its condition; a torque

check of the small and large jam nuts on

the tab control rod, if necessary; and

corrective actions, as applicable. For

certain airplanes, this AD also requires

a one-time inspection for torque of the

small and large jam nuts on the tab

control rods; and corrective actions, as

applicable. This action is prompted by

reports indicating that operators found

problems with the elevator tab control

rods during accomplishment of an

existing AD. The actions specified by

this AD are intended to prevent

excessive freeplay in the tab control

mechanism, which could result in

elevator tab flutter and consequent loss

of controllability of the airplane.

DATES: Effective June 18, 2001, to all

persons except those persons to whom

it was made immediately effective by

emergency AD 2001–09–51, issued

April 24, 2001, 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 18,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

August 10, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2001–NM–

126–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 p.m.,

Monday through Friday, except Federal

holidays. Comments may be submitted

via fax to (425) 227–1232. Comments

may also be sent via the Internet using

the following address: 9-anmiarcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2001–NM–126–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

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:

Kenneth J. Fairhurst, Aerospace

Engineer, Systems and Equipment

Branch, ANM–130S, FAA, Seattle

Aircraft Certification Office, 1601 Lind

Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–1118;

fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: On April

24, 2001, the FAA issued emergency AD

2001–09–51, which is applicable to

certain Boeing Model 737–600, –700,

–700C, and –800 series airplanes.

That action was prompted by reports

indicating that, during accomplishment

of actions required by AD 2001–04–08,

amendment 39–12127 (66 FR 13229,

March 5, 2001), operators found

problems with the elevator tab control

rods on certain Boeing Model 737–700

and –800 series airplanes. One operator

found jam nuts that had been installed

improperly. Two other operators

reported damage that was attributed to

inadequately torqued jam nuts. The

control rod jam nuts may not have been

torqued properly when the control rod

length was rigged at Boeing prior to

delivery of the airplanes.

Improperly torqued jam nuts on the

elevator tab control rods could result in

damage to the tab control rod. If both tab

control rods are damaged, excessive

freeplay in the tab control mechanism

can occur, which could result in

elevator tab flutter. This condition, if

not corrected, could result in loss of

controllability of the airplane.

The elevator tab control rods on

Model 737–600 and –700C series

airplanes are identical to those on the

affected Model 737–700 and –800 series

airplanes. Therefore, those Model 737–

600 and –700C series airplanes may be

31142 Federal Register / Vol. 66, No. 112 / Monday, June 11, 2001 / Rules and Regulations

subject to the same unsafe condition

revealed on Model 737–700 and –800

series airplanes.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Alert Service Bulletin 737–

27A1245, dated April 23, 2001, which

describes procedures for inspecting the

small jam nut on the elevator tab control

rods to detect inspection putty and to

determine its condition; a torque check

of the small and large jam nuts on the

tab control rod, if necessary; and

corrective actions (including performing

a detailed visual inspection of the

threads on the rod end bearing for wear,

measuring the diameter of the threads

on the rod end bearing, replacing the

rod end bearing and the threaded

adjustment bushing, torquing the jam

nuts, and applying inspection putty), as

applicable.

For any control rod jam nut on which

the putty is found and is intact, the alert

service bulletin also describes

procedures for a one-time inspection for

torque of the small and large jam nuts

on the tab control rods; and corrective

actions (including performing a detailed

visual inspection of the threads on the

rod end bearing for wear, measuring the

diameter of the threads on the rod end

bearing, replacing the rod end bearing

and the threaded adjustment bushing,

torquing the jam nuts, and applying

inspection putty), as applicable.

Explanation of Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of this same

type design, this airworthiness directive

is issued to require the actions specified

in the alert service bulletin described

previously. The actions are required to

be accomplished in accordance with the

alert service bulletin described

previously.

This AD also requires that operators

report both positive and negative results

of inspections to Boeing.

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 April 24, 2001, to all

known U.S. owners and operators of

Boeing Model 737–600, –700, –700C,

and –800 series airplanes. 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.

Clarification of Applicability

For clarification, the FAA notes that,

while the alert service bulletin does not

specify that Model 737–700C series

airplanes are subject to the actions in

the alert service bulletin, the list of

affected line numbers in the

applicability of this AD includes the

line numbers of certain Model 737–

700C series airplanes.

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 2001–NM–126–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. 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:

2001–09–51 Boeing: Amendment 39–12251.

Docket 2001–NM–126–AD.

Applicability: Model 737–600, –700,

–700C, and –800 series airplanes, line

numbers 1 through 788 inclusive, 790

through 814 inclusive, 816, 819, 821, and

823, 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 (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

Federal Register / Vol. 66, No. 112 / Monday, June 11, 2001 / Rules and Regulations 31143

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent excessive freeplay in the tab

control mechanism, which could result in

elevator tab flutter, and consequent loss of

controllability of the airplane, accomplish

the following:

Inspection and Corrective Actions

(a) Within 10 days after the effective date

of this AD, inspect the small jam nut on the

elevator tab control rods to detect inspection

putty and to determine its condition, per

paragraph III.B. of the Accomplishment

Instructions of Boeing Alert Service Bulletin

737–27A1245, dated April 23, 2001.

(1) If inspection putty is found and it is

intact, no further action is required by

paragraph (a) of this AD.

(2) If inspection putty is missing or

detached, prior to further flight, perform a

torque check of the small and large jam nuts

on the tab control rod, in accordance with

paragraph III.B. of the alert service bulletin.

Prior to further flight, perform corrective

actions (including performing a detailed

visual inspection of the threads on the rod

end bearing for wear, measuring the diameter

of the threads on the rod end bearing,

replacing the rod end bearing and the

threaded adjustment bushing, torquing the

jam nuts, and applying inspection putty), as

applicable, per paragraph III.B. of the alert

service bulletin. If the tab control rod is

disassembled and if no wear is found during

accomplishment of the detailed visual

inspection specified in this paragraph,

measuring the diameter of the threads on the

rod end bearing may be deferred until 250

flight cycles or 30 days after the effective date

of this AD, whichever occurs first.

Note 2: For the purposes of this AD, a

detailed visual 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.’’

(b) For any control rod jam nut on which

the putty was found and was intact, as

specified in paragraph (a)(1) of this AD:

Within 250 flight cycles or 30 days after the

effective date of this AD, whichever occurs

first, perform a one-time inspection for

torque of the small and large jam nuts on the

tab control rods, per paragraph III.C. of the

Accomplishment Instructions of Boeing Alert

Service Bulletin 737–27A1245, dated April

23, 2001. Prior to further flight, perform

corrective actions (including performing a

detailed visual inspection of the threads on

the rod end bearing for wear, measuring the

diameter of the threads on the rod end

bearing, replacing the rod end bearing and

the threaded adjustment bushing, torquing

the jam nuts, and applying inspection putty),

as applicable, per paragraph III.C. of the alert

service bulletin.

Reporting Requirement

(c) Within 15 days after accomplishing the

inspections required by paragraphs (a) and

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

findings, positive or negative, to Boeing per

paragraph I.C. of the Planning Information of

Boeing Alert Service Bulletin 737–27A1245,

dated April 23, 2001. 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.

Alternative Methods of Compliance

(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, 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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Incorporation by Reference

(e) The actions shall be done in accordance

with Boeing Alert Service Bulletin 737–

27A1245, dated April 23, 2001. 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

June 18, 2001, to all persons except those

persons to whom it was made immediately

effective by emergency AD 2001–09–51,

issued on April 24, 2001, which contained

the requirements of this amendment.

Issued in Renton, Washington, on May 25,

2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–13997 Filed 6–8–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–135–AD; Amendment

39–12252; AD 2001–11–09]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A330 and A340 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Airbus Model

A330 and A340 series airplanes. This

action requires repetitive inspections to

detect discrepancies of the transfer

tubes and the collar of the ball nut of the

trimmable horizontal stabilizer actuator

(THSA); and corrective action, if

necessary. This action is necessary to

prevent degraded operation of the THSA

due to the entrance of water into the ball

nut. Degraded operation could lead to

reduced controllability of the airplane.

This action is intended to address the

identified unsafe condition.

DATES: Effective June 26, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 26,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

July 11, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2001–NM–

135–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays. Comments may be

submitted via fax to (425) 227–1232.

Comments may also be sent via the

Internet using the following address: 9-

anm-iarcomment@faa.gov. Comments

sent via fax or the Internet must contain

‘‘Docket No. 2001–NM–135–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

The service information referenced in

this AD may be obtained from Airbus

Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.