23834 Federal Register / Vol. 66, No. 91 / Thursday, May 10, 2001 / Rules and Regulations

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–CE–22–AD; Amendment

39–12223; AD 2001–09–16]

RIN 2120–AA64

Airworthiness Directives; Eagle

Aircraft Pty. Ltd. Model 150B Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Eagle Aircraft Pty. Ltd.

(Eagle) Model 150B airplanes. This AD

requires you to inspect the rudder

cables for fraying, broken strands, etc.

(referred to as damage), and replace any

damaged cables. This AD also requires

you to replace the rudder cable pulleys

with larger diameter pulleys to

eliminate the possibility of further

damage. This AD is the result of

mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for Australia.

The actions specified by this AD are

intended to detect and correct damaged

rudder cables caused by chafing of the

cable against the pulleys. Continued

airplane operation with damaged cables

could result in rudder cable system

failure with possible loss of airplane

control.

DATES: This AD becomes effective on

June 29, 2001.

The Director of the Federal Register

approved the incorporation by reference

of certain publications listed in the

regulations as of June 29, 2001.

ADDRESSES: You may get the service

information referenced in this AD from

Eagle Aircraft Pty. Ltd., Lot 700

Cockburn Road, Henderson WA 6166

Australia; telephone: (08) 9410 1077;

facsimile: (08) 9410 2430. You may

examine this information at the Federal

Aviation Administration (FAA), Central

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 2000–CE–

22–AD, 901 Locust, Room 506, Kansas

City, Missouri 64106; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Fredrick A. Guerin, Aerospace Engineer,

FAA, Los Angeles Aircraft Certification

Office, 3960 Paramount Boulevard,

Lakewood, California 90712; telephone:

(562) 627–5232; facsimile: (562) 627–

5210.

SUPPLEMENTARY INFORMATION:

Discussion

What Events Have Caused This AD?

The Civil Aviation Safety Authority

(CASA), which is the airworthiness

authority for Australia, notified FAA

that an unsafe condition may exist on

certain Eagle Model 150B airplanes. The

CASA reports an occurrence where

frayed rudder cables were found on an

Eagle Model 150B airplane. Further

investigation reveals that the diameter

of the rudder cable pulleys is too small

and cables rub against these pulleys.

What Are the Consequences If the

Condition Is Not Corrected?

Continued airplane operation with

damaged cables could result in rudder

cable system failure with possible loss

of airplane control.

Has FAA Taken Any Action To This

Point?

We issued a proposal to amend part

39 of the Federal Aviation Regulations

(14 CFR part 39) to include an AD that

would apply to certain Eagle Model

150B airplanes. This proposal was

published in the Federal Register as a

notice of proposed rulemaking (NPRM)

on January 2, 2001 (66 FR 59). The

NPRM proposed to require you to:

—Inspect the rudder cables for fraying,

broken strands, etc. (referred to as

damage), and replace any damaged

cables; and

—Replace the rudder cable pulleys with

larger diameter pulleys to eliminate

the possibility of further damage.

Was the Public Invited To Comment?

Interested persons were afforded an

opportunity to participate in the making

of this amendment. We have given due

consideration to the comment received.

Comment Disposition

What Is the Commenter’s Concern?

Eagle Aircraft Pty. Ltd requests that

FAA withdraw the AD because pulley

replacement kits to correct the unsafe

condition have been shipped to the

United States and all affected airplanes

models may already be in compliance

with this AD.

What Is FAA’s Response To the

Concern?

We do not concur. Although there

may be airplanes on the U.S. Register

that have already incorporated the kit

installation, the AD is still justified.

Issuing an AD is the only way to assure

that:

—The installation of the pulley

replacement kit is incorporated on

any U.S.-registered airplane;

—The actions are accomplished on any

airplane that is imported from another

country and placed on the U.S.

Register; and

—The installation continues to be

incorporated on all U.S. registered

airplanes.

We have not changed the AD as a

result of this comment.

FAA’s Determination

What Is FAA’s Final Determination on

This Issue?

After careful review of all available

information related to the subject

presented above, we have determined

that air safety and the public interest

require the adoption of the rule as

proposed except for minor editorial

corrections. We determined that these

minor corrections:

—Will not change the meaning of the

AD; and

—Will not add any additional burden

upon the public than was already

proposed.

Cost Impact

How Many Airplanes Does This AD

Impact?

We estimate that this AD affects 5

airplanes in the U.S. registry.

What Is the Cost Impact of This AD on

Owners/Operators of the Affected

Airplanes?

We estimate the following costs to

accomplish the inspection of the rudder

cable and replacement of the rudder

cable pulley:

Labor cost Parts cost Total cost

per airplane

Total cost

on U.S.

operators

5 workhours × $60 ................................................................................................................................... $286 $586 $2,930

Federal Register / Vol. 66, No. 91 / Thursday, May 10, 2001 / Rules and Regulations 23835

Replacement cables, if necessary, will

cost $305 perairplane. We have no way

of determining the number of rudder

cables that will be found damaged

during the inspection.

Compliance Time of this AD

What Is the Compliance Time of This

AD?

The compliance time of this AD will

be to accomplish the inspection and

rudder cable pulley replacement

‘‘within the next 100 hours time-inservice (TIS) after the effective date of

this AD’’ and to accomplish any

necessary cable replacement ‘‘prior to

further flight after the inspection.’’

Why Are the Compliance Times of the

Australian AD Different From the

Compliance Times in This AD?

The Australian AD requires (on Eagle

Model 150B airplanes registered in

Australia) the inspection within the

next 5 hours of service and requires the

pulley replacement within 100 hours of

operation. These are the compliance

times specified in the service

information.

We do not have justification to require

the inspection within 5 hours of service.

We use compliance times such as this

when we have identified an urgent

safety of flight situation. We believe that

100 hours TIS will give the owners/

operators of the affected airplanes

enough time to have the inspection and

replacement accomplished without

compromising the safety of the

airplanes.

By accomplishing both the inspection

and replacement at the same time, the

owners/operators of the affected

airplanes only have their airplanes out

of service once instead of twice.

Regulatory Impact

Does This AD Impact Various Entities?

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.

Does This AD Involve a Significant Rule

or Regulatory Action?

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 copy of the final

evaluation prepared for this action is

contained in the Rules Docket. A copy

of it may be obtained by contacting 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, under 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. FAA amends § 39.13 by adding a

new AD to read as follows:

2001–09–16 Eagle Aircraft Pty. Ltd.:

Amendment 39–12223; Docket No.

2000–CE–22–AD.

(a) What airplanes are affected by this AD?

This AD affects Model 150B airplanes, serial

numbers 001 through 030, that are

certificated in any category.

(b) Who must comply with this AD?

Anyone who wishes to operate any of the

above airplanes must comply with this AD.

(c) What problem does this AD address?

The actions specified by this AD are intended

to detect and correct damaged rudder cables

caused by chafing of the cable against the

pulleys. Continued airplane operation with

damaged cables could result in rudder cable

system failure with possible loss of airplane

control.

(d) What actions must I accomplish to

address this problem? To address this

problem, you must accomplish the following:

Actions Compliance Procedures

(1) Inspect the rudder cables for fraying, broken

strands, etc. (referred to as damage).

Within the next 100 hours time-in-service

(TIS) after June 29, 2001 (the effective date

of this AD).

In accordance with Eagle Service Bulletin No.

1059, dated January 21, 1999.

(2) Replace any rudder cables found damaged

during the inspection.

Prior to further flight after the inspection ......... In accordance with the instructions in the

maintenance manual, as specified in Eagle

Service Bulletin No. 1059, dated January

21, 1999.

(3) Replace the rudder cable pulleys with new

rudder cable pulleys, part numbers

MS20220–1 and MS20220–2, change pulley

attachment, and reduce cable tension.

Prior to further flight after the inspection ......... In accordance with Eagle Service Bulletin No.

1076, Revision 2, dated December 14,

1999.

(4) Do not install any rudder cable pulleys that

are not part numbers MS20220–1 and

MS20220–2 (with all associated hardware).

As of June 29, 2001 (the effective date of this

AD).

Not applicable.

(e) Can I comply with this AD in any other

way? You may use an alternative method of

compliance or adjust the compliance time if:

(1) Your alternative method of compliance

provides an equivalent level of safety; and

(2) The Manager, Los Angeles Aircraft

Certification Office (ACO), approves your

alternative. Submit your request through an

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Los Angeles ACO.

Note 1: This AD applies to each airplane

identified in paragraph (a) of this AD,

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 (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 you have not

eliminated the unsafe condition, specific

actions you propose to address it.

23836 Federal Register / Vol. 66, No. 91 / Thursday, May 10, 2001 / Rules and Regulations

(f) Where can I get information about any

already-approved alternative methods of

compliance? Contact Fredrick A. Guerin,

Aerospace Engineer, FAA, Los Angeles

Aircraft Certification Office, 3960 Paramount

Boulevard, Lakewood, California 90712;

telephone: (562) 627–5232; facsimile: (562)

627–5210.

(g) What if I need to fly the airplane to

another location to comply with this AD? The

FAA can issue a special flight permit under

sections 21.197 and 21.199 of the Federal

Aviation Regulations (14 CFR 21.197 and

21.199) to operate your airplane to a location

where you can accomplish the requirements

of this AD.

(h) Are any service bulletins incorporated

into this AD by reference? Actions required

by this AD must be done in accordance with

Eagle Service Bulletin No. 1059, dated

January 21, 1999, and Eagle Service Bulletin

No. 1076, Rev. 2, dated December 14, 1999.

The Director of the Federal Register approved

this incorporation by reference under 5

U.S.C. 552(a) and 1 CFR part 51. You can get

copies from Eagle Aircraft Pty. Ltd., Lot 700

Cockburn Road, Henderson WA 6166

Australia. You can look at copies at the FAA,

Central Region, Office of the Regional

Counsel, 901 Locust, Room 506, Kansas City,

Missouri, or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(i) When does this amendment become

effective? This amendment becomes effective

on June 29, 2001.

Note 2: The subject of this AD is addressed

in Australian AD Number X–TS/2, effective

December 24, 2000.

Issued in Kansas City, Missouri, on May 1,

2001.

James E. Jackson,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–11457 Filed 5–9–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–85–AD; Amendment

39–12222; AD 2001–09–15]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 737–200 and –300 Series

Airplanes Equipped with Cargo Doors

Installed in Accordance With

Supplemental Type Certificate (STC)

SA2969SO

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Boeing Model 737–

200 and –300 series airplanes, that

currently requires repetitive inspections

to detect cracking in the radii on the

support angles on the lower jamb (latch

lug fittings) of the main deck cargo door,

and replacement of cracked parts. This

amendment adds a requirement for

installation of redesigned lower jamb

latch support angles in the main cargo

door surround structure, which would

terminate the repetitive inspections.

This amendment is prompted by the

development of a modification that will

provide better protection of the subject

area against effects of structural fatigue.

The actions specified by this AD are

intended to prevent in-flight separation

of the main deck cargo door from the

airplane due to fatigue cracking on the

support angles on the lower door jamb.

DATES: Effective June 14, 2001.

The incorporation by reference of

Pemco Service Bulletin 737–53–0003,

Revision 4, dated February 22, 1995;

and Pemco Service Bulletin 737–53–

0003, Revision 5, dated March 25, 1999;

as listed in the regulations, is approved

by the Director of the Federal Register

as of June 14, 2001.

The incorporation by reference of

Pemco Alert Service Letter 737–53–

0003, Revision 3, dated December 22,

1994, as listed in the regulations, was

approved previously by the Director of

the Federal Register as of January 24,

1995 (60 FR 2323, January 9, 1995).

ADDRESSES: The service information

referenced in this AD may be obtained

from Pemco Aeroplex, Inc., P.O. Box

2287, Birmingham, Alabama 35201–

2287. 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 FAA, Atlanta

Aircraft Certification Office, One Crown

Center, 1895 Phoenix Boulevard, suite

450, Atlanta, Georgia; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

William Culler, Airframe and

Propulsion Branch, ACE–117A, FAA,

Atlanta Aircraft Certification Office,

One Crown Center, 1895 Phoenix

Boulevard, suite 450, Atlanta, Georgia

30337–2748; telephone (770) 703–6084;

fax (770) 703–6097.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 95–01–06 R1,

amendment 39–9449 (60 FR 62192,

December 5, 1995), which is applicable

to certain Boeing Model 737–200 and

–300 series airplanes, was published in

the Federal Register on November 22,

1999 (64 FR 63757). The action

proposed to continue to require

repetitive inspections to detect cracking

in the radii on the support angles on the

lower jamb (latch lug fittings) of the

main deck cargo door, and replacement

of cracked parts. That action also adds

a requirement for installation of

redesigned lower jamb latch support

angles in the main cargo door surround

structure, which would terminate the

repetitive inspections.

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. Two commenters

state that the airplanes they operate

would not be affected by the proposed

rule.

Include Additional Service Information

One commenter asks that Pemco

Service Bulletin 737–53–0005, dated

November 18, 1997, which specifies

alignment of the door latch base and

frames, be included as an alternative

method of compliance in paragraph

(c)(1) of the proposed rule. The

commenter also asks that the actions

specified in that service bulletin be

added to the proposed rule as

terminating action for the requirements

of AD 95–01–06 R1 (above). The

commenter states that its fleet was

modified per the service bulletin

referenced in the proposed rule, but one

airplane was misaligned between the

door latch base and fuselage framing at

FS 490.8. The commenter accomplished

the alignment specified in service

bulletin 737–53–0005.

The FAA does not concur with the

commenter’s requests. The FAA does

not find it necessary to revise this AD

to include special instructions for

airplanes modified with another service

bulletin. Operators should note that

most AD actions address modifications

affecting the subject area of the AD

using the note that appears as Note 1 of

this AD, which states, ‘‘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

(AMOC) in accordance with paragraph

(c)(1) of this AD.’’ The AMOC letter

would be issued to the operator by the

appropriate office, as stated in

paragraph (c)(1).

Additionally, the service bulletin

referenced in the final rule specifies

installation of redesigned lower jamb

latch support angles in the main cargo

door surround structure, which would

terminate the repetitive inspections.