42206 Federal Register / Vol. 63, No. 152 / Friday, August 7, 1998 /Rules and Regulations

Cost Impact

The FAA estimates that 80 airplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

3 workhours per airplane to accomplish

this action, and that the average labor

rate is approximately $60 an hour. Parts

cost approximately $10 per airplane.

Based on these figures, the total cost

impact of this AD on U.S. operators is

estimated to be $15,200, or $190 per

airplane.

Regulatory Impact

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

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, 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 a new airworthiness directive

(AD) to read as follows:

98–16–14 Pilatus Britten-Norman Ltd:

Amendment 39–10690; Docket No. 97-

CE–112–AD.

Applicability: Models BN–2, BN–2A, BN–

2A–3, BN–2A–6, N–2A–8, BN–2A–2, BN–

2A–9, BN–2A–20, BN–2A–21, BN–2A–26,

BN–2A–27, BN–2B–20, BN–2B–21, BN–2B–

26, BN–2B–27, and BN–2T airplanes, all

serial numbers, 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 within the next 50

landings after the effective date of this AD,

unless already accomplished.

Note 2: The compliance time of this AD is

presented in landings instead of hours timein-service (TIS). If the number of landings is

unknown, hours TIS may be used by

multiplying the number of hours TIS by 1.5.

To prevent the bolts that attach the lower

fitting of the main landing gear (MLG) to the

nacelle from becoming threadbound, which

could result in structural failure of the MLG

with consequent loss of control of the

airplane during takeoff, taxi, or landing

operations, accomplish the following:

(a) Replace the attachment bolts, nuts, and

washers of the lower fitting of the MLG, in

accordance with Pilatus Britten-Norman

Service Bulletin No. BN2/SB.231, Issue 2,

dated October 1, 1997.

(b) 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

an be accomplished.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Small Airplane

Directorate, 1201 Walnut, suite 900, Kansas

City, Missouri, 64106. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Small Airplane Directorate.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane

Directorate.

(d) Questions or technical information

related to Pilatus Britten-Norman Service

Bulletin BN2/SB.231, Issue 2, dated October

1, 1997, should be directed to Pilatus BrittenNorman Limited, Bembridge, Isle of Wight,

United Kingdom PO35 5PR; telephone: 44–

1983 872511; facsimile: 44–1983 873246.

This service information may be examined at

the FAA, Central Region, Office of the

Regional Counsel, Room 1558, 601 E. 12th

Street, Kansas City, Missouri 64106.

(e) The replacement required by this AD

shall be done in accordance with Pilatus

Britten-Norman Service Bulletin No. BN2/

SB.231, Issue 2, dated October 1, 997. 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 Pilatus

Britten-Norman Limited, Bembridge, Isle of

Wight, United Kingdom PO35 5PR. Copies

may be inspected at the FAA, Central Region,

ffice of the Regional Counsel, Room 1558,

601 E. 12th Street, Kansas City, Missouri, or

at the Office of the Federal Register, 800

North Capitol Street, NW, suite 700,

Washington, DC.

Note 4: The subject of this AD is addressed

in British AD No. 008–10–96, dated January

31, 1997.

(f) This amendment becomes effective on

September 21, 1998.

Issued in Kansas City, Missouri, on July 28,

1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–20837 Filed 8–6–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–208–AD; Amendment

39–10693; AD 98–16–17]

RIN 2120–AA64

Airworthiness Directives; Cessna

Model 750 Citation X 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 all Cessna Model 750

Citation X series airplanes. This action

requires repetitive in-flight functional

tests to verify proper operation of the

secondary horizontal stabilizer pitch

trim system, and repair, if necessary.

This amendment is prompted by reports

of simultaneous failures of the primary

and secondary horizontal stabilizer

pitch trim system during flight, due to

internal water contamination and

corrosion damage in the system

actuator. The actions specified in this

AD are intended to detect and correct
Federal Register / Vol. 63, No. 152 / Friday, August 7, 1998 /Rules and Regulations 42207

such contamination and damage, which

could result in simultaneous failure of

both primary and secondary pitch trim

systems, and consequent reduced

controllability of the airplane.

DATES: Effective August 24, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 24,

1998.

Comments for inclusion in the Rules

Docket must be received on or before

October 6, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98-NM–

208-AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from Cessna

Aircraft Co., P.O. Box 7706, Wichita,

Kansas 67277. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at

the FAA, Small Airplane Directorate,

Wichita Aircraft Certification Office,

1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas; or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Joel

M. Ligon, Aerospace Engineer, Systems

and Propulsion Branch, ACE–116W,

FAA, Small Airplane Directorate,

Wichita Aircraft Certification Office,

1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas

67209; telephone (316) 946–4138; fax

(316) 946–4407.

SUPPLEMENTARY INFORMATION: The FAA

recently received reports of

simultaneous primary and secondary

horizontal stabilizer pitch trim system

failures during flight on Cessna Model

750 Citation X series airplanes.

Inspection of the horizontal stabilizer

pitch trim actuators utilized for both

primary and secondary pitch trim has

revealed evidence of internal water

contamination and corrosion damage.

This condition may be caused by water

being ingested into the actuator due to

condensation during airplane descent

from high altitude into a warm, humid

environment. Subsequent testing by the

manufacturer has verified that the

trapped water may freeze in the actuator

mechanism and disable actuation of

both primary and secondary trim. It has

been determined that the actuator case

seal, as applied to some actuators, may

be ineffective at preventing internal

water contamination and corrosion

damage. Such contamination and

damage, if not corrected, could result in

simultaneous failure of both primary

and secondary trim system, and

consequent reduced controllability of

the airplane.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Cessna Alert Service Bulletin ASB750–

27–22, dated July 2, 1998, which

describes procedures for repetitive inflight functional tests to verify proper

operation of the secondary horizontal

stabilizer pitch trim system. (Such

functional testing of the primary

horizontal stabilizer pitch trim system is

currently addressed in the FAAapproved Airplane Flight Manual and

FAA-approved maintenance procedures

for these airplanes.) For airplanes on

which the functional test fails, the alert

service bulletin also describes

procedures for inspection of the actuator

components and clutch assemblies for

evidence of internal water

contamination in the system actuator

and corrosion damage; and repair, if

necessary.

Explanation of the Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design, this AD is being issued to

prevent failure of both primary and

secondary pitch trim systems due to

internal water contamination and

corrosion damage in the system

actuator, which could result in reduced

controllability of the airplane. This AD

requires accomplishment of the actions

specified in the alert service bulletin

described previously.

Interim Action

This is considered to be interim

action until final action is identified, at

which time the FAA may consider

further rulemaking.

Determination of Rule’s Effective Date

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.

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 98–NM–208–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

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
42208 Federal Register / Vol. 63, No. 152 / Friday, August 7, 1998 /Rules and Regulations

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:

98–16–17 Cessna Aircraft Company:

Amendment 39–10693. Docket 98–NM–

208–AD.

Applicability: All Model 750 Citation X

series airplanes, 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 detect and correct internal water

contamination and corrosion damage of the

secondary horizontal stabilizer trim actuator,

which could result in simultaneous failure of

both primary and secondary pitch trim

systems, and consequent reduced

controllability of the airplane, accomplish

the following:

(a) Within 10 days after the effective date

of this AD, perform an in-flight functional

test to verify proper operation of the

secondary horizontal stabilizer pitch trim

system, in accordance with Cessna Alert

Service Bulletin ASB750–27–22, dated July

2, 1998.

(1) If the secondary trim system does not

fail during the in-flight functional test, repeat

the action thereafter at intervals not to exceed

30 days.

(2) If the secondary trim system fails

during the in-flight functional test, prior to

next flight, inspect the actuator components

and clutch assemblies for evidence of

internal water contamination or corrosion

damage in accordance with the alert service

bulletin. If any evidence of internal water

contamination or corrosion damage is

detected, prior to further flight, repair in

accordance with the alert service bulletin.

Repeat the in-flight functional test thereafter

at intervals not to exceed 30 days.

(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, Wichita

Aircraft Certification Office (ACO), FAA,

Small Airplane Directorate. Operators shall

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Wichita ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(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.

(d) The actions shall be done in accordance

with Cessna Alert Service Bulletin ASB750–

27–22, dated July 2, 1998. 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 Cessna Aircraft Co., P.O.

Box 7706, Wichita, Kansas 67277. Copies

may be inspected at the FAA, Transport

Airplane Directorate, 1601 Lind Avenue,

SW., Renton, Washington; or at the FAA,

Small Airplane Directorate, Wichita Aircraft

Certification Office, 1801 Airport Road,

Room 100, Mid-Continent Airport, Wichita,

Kansas; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(e) This amendment becomes effective on

August 24, 1998.

Issued in Renton, Washington, on July 29,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–20836 Filed 8–6–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–227–AD; Amendment

39–10694; AD 98–16–18]

RIN 2120–AA64

Airworthiness Directives; Learjet

Model 60 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 Learjet Model 60

airplanes. This action requires repetitive

measurements of the brake wear

dimension between the housing

subassembly and the pressure plate that

is adjacent to the top pistons of the

brake assembly; and follow-on

corrective actions, if necessary. This

amendment is prompted by reports of

abnormal (uneven) brake wear. The

actions specified in this AD are

intended to detect and repair an

abnormal brake wear condition, which

could result in loss of brake

effectiveness and cause the airplane to

leave the runway surface.

DATES: Effective August 24, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 24,

1998.

Comments for inclusion in the Rules

Docket must be received on or before

October 6, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

227–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from Aircraft

Braking Systems Corporation, 1204

Massillon, Akron, Ohio 44306. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Small

Airplane Directorate, Wichita Aircraft

Certification Office, 1801 Airport Road,

Room 100, Mid-Continent Airport,

Wichita, Kansas; or at the Office of the

Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT: Paul

C. DeVore, Aerospace Engineer, Systems

and Propulsion Branch, ACE–116W,

FAA, Small Airplane Directorate,

Wichita Aircraft Certification Office,

1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas

67209; telephone (316) 946–4142; fax

(316) 946–4407.

SUPPLEMENTARY INFORMATION: The FAA

has received reports from Learjet of an

abnormal brake wear condition on

certain Learjet Model 60 airplanes.

Subsequent investigation, conducted by

Aircraft Braking Systems Corporation

(ABS) (the manufacturer of the brakes),

revealed an abnormal (uneven) brake