600 Federal Register / Vol. 62, No. 3 / Monday, January 6, 1997 / Rules and Regulations

Done in Washington, DC, this 26th day of

December 1996.

Al Strating,

Acting Administrator, Animal and Plant

Health Inspection Service.

[FR Doc. 97–177 Filed 1–3–97; 8:45 am]

BILLING CODE 3410–34–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–ANE–39; Amendment 39–

9875; AD 97–01–05]

RIN 2120–AA64

Airworthiness Directives; Williams

International, L.L.C. Model FJ44–1A

Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to Williams International,

L.L.C. Model FJ44–1A turbofan engines.

This action requires initial and

repetitive eddy current inspections (ECI)

for possible cracks in high pressure

turbine (HPT) disk blade retention

posts. In addition, this AD requires the

installation of advanced design HPT

disks as terminating action to the

inspection requirements of this AD.

This amendment is prompted by two

incidents of HPT disk blade retention

post separations. The actions specified

in this AD are intended to locate

possible cracks in HPT disk blade

retention posts, thereby preventing the

separation of these posts and the

liberation of the turbine blades that they

retain, and a subsequent loss of engine

power. In addition, the actions specified

in this AD are intended to prevent the

possible high disk speed uncontained

liberation of disk posts and turbine

blades, which could cause aircraft

damage.

DATES: Effective January 21, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 21,

1997.

Comments for inclusion in the Rules

Docket must be received on or before

March 7, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

96–ANE–39, 12 New England Executive

Park, Burlington, MA 01803–5299.

The service information referenced in

this AD may be obtained from Mr. John

Teeter, Manager, Customer Support,

Williams International, 2280 West

Maple Road, P.O. Box 200, Walled Lake,

MI 48390–0200; telephone (810) 624–

5200, fax (810) 669–9515. This

information may be examined at the

FAA, New England Region, Office of the

Assistant Chief 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.

FOR FURTHER INFORMATION CONTACT:

Eugene H. Messal, Aerospace Engineer,

Chicago Aircraft Certification Office,

FAA, Small Airplane Directorate, 2300

East Devon Avenue, Des Plaines, Illinois

60018; telephone (847) 294–7011, fax

(847) 294–7834.

SUPPLEMENTARY INFORMATION: The

Federal Aviation Administration (FAA)

has verified two reports of inflight HPT

disk post separations on Williams

International model FJ44–1A turbofan

engines. One of these inflight post

separations was uncontained. The

investigation revealed that in both cases,

high pressure turbine (HPT) disk blade

retention posts separated due to

cracking caused by material creep/

fatigue. This condition, if not corrected,

could result in other engines

experiencing HPT disk blade retention

post separations and turbine blade

liberations, and subsequent losses of

engine power. In addition, this

condition could, if not corrected, result

in other engines experiencing high disk

speed uncontained liberation of disk

posts and turbine blades, which could

cause aircraft damage.

The FAA has reviewed and approved

the technical contents of Williams-Rolls

Alert Service Bulletin (ASB) No. FJ44–

A72–30, dated November 6, 1996, that

describes procedures for eddy current

inspections (ECI) for possible cracks in

HPT disk blade retention posts; and

ASB No. FJ44–A72–31, dated November

4, 1996, that describes procedures for

replacement of existing HPT disks with

advanced design HPT disks.

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of the same

design, this AD is being issued to locate

possible cracks in HPT disk blade

retention posts, which could lead to the

liberation of the turbine blades that they

retain, and subsequent loss of engine

power. In addition, this AD is being

issued to prevent the separation of HPT

disk posts that could lead to a high disk

speed uncontained liberation of disk

posts and turbine blades, which could

result in aircraft damage. This AD

requires initial and repetitive ECI for

possible cracks in HPT disk blade

retention posts. The inspection

population is divided into two groups,

with the higher risk group listed by

engine serial number (S/N). This group

of HPT disks is at a higher risk due to

a lower stress rupture strength

characteristic. In addition, this AD

requires replacement of the existing

HPT disks, Part Number (P/N) 48629,

with advanced design HPT disks, P/N

55291, by July 1, 1997, as terminating

action to the inspection requirements of

this AD. The calendar end-dates for this

AD were determined based upon each

suspect disk group’s time to crack

initiation, subsequent crack propagation

rate, and its failure probability. In

addition, the total in-service cycles and

hours of each of the suspect disks of

both groups, and the ASB replacement

parts availability were contributing

factors for determining the end-dates.

These actions are required to be

accomplished in accordance with the

ASBs described previously.

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 should 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,
Federal Register / Vol. 62, No. 3 / Monday, January 6, 1997 / Rules and Regulations 601

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 notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 96–ANE–39.’’ The

postcard will be date stamped and

returned to the commenter.

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 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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

97–01–05 Williams International, L.L.C.:

Amendment 39–9875. Docket 96–ANE–

39.

Applicability: Williams International L.L.C.

Model FJ44–1A turbofan engines, with serial

numbers 1001–1179, 1196, and 1197,

installed on, but not limited to, Cessna

Citation Model 525 aircraft.

Note 1: This airworthiness directive (AD)

applies to each engine 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 engines 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 possible high pressure turbine

(HPT) disk blade retention post separations

and the release of their retained turbine

blades, subsequent loss of engine power, and

possible high disk speed uncontained

liberation of disk posts and the turbine

blades, which could cause aircraft damage,

accomplish the following:

(a) Perform initial and repetitive eddy

current inspections (ECI) for cracks in HPT

disks, Part Number (P/N) 48629, blade

retention posts in accordance with the

following schedule and requirements:

Engine serial Nos. Initial compliance required Repetitive inspection required

1001, 1004–1010, 1016, 1017, 1020, 1023–1026, 1031, 1033, 1036,

1039, 1041, 1042, 1043, 1046–1048, 1051–1056, 1063, 1069,

1071, 1072, 1076, 1080, 1082, 1091, 1092, 1095–1098, 1107,

1108, 1111, 1125, 1127–1129, 1133, 1134, 1165, 1172, 1178

Within 50 cycles after the effective

date of this AD or by February

1, 1997, whichever occurs first.

Thereafter, at intervals not to exceed 125 cycles in service (CIS)

since last inspection.

Remaining serial number engines with 575 CIS or more as of April 1,

1997

No later than May 1, 1997 ............. Thereafter, at intervals not to exceed 125 CIS since last inspection.

(1) Perform the initial and repetitive eddy

current inspections for cracks in HPT disk

blade retention posts in accordance with

Williams-Rolls Alert Service Bulletin (ASB)

No. FJ44–A72–30, dated November 6, 1996.

(2) Remove from service HPT disks that do

not meet the ‘‘return to service’’ criteria

stated in Williams-Rolls ASB No. FJ44–A72–

30, dated November 6, 1996, and replace

them with serviceable HPT disks, P/N 48629,

that meet the required ASB ‘‘return to

service’’ criteria, or replace them with

advanced design HPT disks, P/N 55291, in

accordance with paragraph (b) of this AD.

(b) No later than July 1, 1997, replace all

existing HPT disks, P/N 48629, with

advanced design HPT disks, P/N 55291, in

accordance with Williams-Rolls ASB No.

FJ44–A72–31, dated November 4, 1996.

Installation of this advanced design HPT disk

constitutes terminating action to the

repetitive inspection requirements of this

AD.

(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, Chicago

Aircraft Certification Office. The request

should be forwarded through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Chicago Aircraft 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 Chicago

Aircraft Certification Office.

(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 aircraft to

a location where the requirements of this AD

can be accomplished.

(e) The actions required by this AD shall

be done in accordance with the following

Williams-Rolls ASBs:

Document No. Pages Date

FJ44–A72–30 ............ 1–7 November

6, 1996.

Total pages: 7

FJ44–A72–31 ............ 1–7 November

4, 1996.

Total pages: 7

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 Mr. John Teeter, Manager, Customer

Support, Williams International, 2280 West

Maple Road, P.O. Box 200, Walled Lake, MI

48390–0200; telephone (810) 624–5200, fax

(810) 669–9515. Copies may be inspected at

the FAA, New England Region, Office of the

Assistant Chief Counsel, 12 New England

Executive Park, Burlington, MA; or at the

Office of the Federal Register, 800 North
602 Federal Register / Vol. 62, No. 3 / Monday, January 6, 1997 / Rules and Regulations

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment becomes effective on

January 21, 1997.

Issued in Burlington, Massachusetts, on

December 27, 1996.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 97–31 Filed 1–3–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–CE–59–AD; Amendment 39–

9873; AD 97–01–02]

RIN 2120–AA64

Airworthiness Directives; Cessna

Aircraft Company Model 525 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Cessna Aircraft

Company (Cessna) Model 525 airplanes.

This action requires repetitively

inspecting the main landing gear (MLG)

trunnion pins for proper installation,

and either immediately or eventually

replacing the existing dry-film

lubricated MLG trunnion slot bearings

with sealed and self-lubricating

bearings. This AD results from an

incident where the left MLG collapsed

during the landing roll even though the

cockpit indications showed that the

MLG was in the normal down and

locked position. Loss of dry-film

lubricant on the MLG trunnion bearings

caused this incident. The actions

specified by this AD are intended to

prevent MLG collapse caused by

trunnion bearing failure, which could

result in loss of control of the airplane

during landing operations.

DATES: Effective January 15, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 15,

1997.

Comments for inclusion in the Rules

Docket must be received on or before

March 7, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Assistant Chief Counsel,

Attention: Rules Docket 96–CE–59–AD,

Room 1558, 601 E. 12th Street, Kansas

City, Missouri 64106.

Service information that applies to

this AD may be obtained from the

Cessna Aircraft Company, Citation

Marketing Division, P.O. Box 7706,

Wichita, Kansas 67277; telephone (316)

941–6000; facsimile (314) 941–8500.

This information may also be examined

at the Federal Aviation Administration

(FAA), Central Region, Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 96–CE–59–AD, Room

1558, 601 E. 12th Street, 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: Mr.

Eual Conditt, Aerospace Safety

Engineer, FAA, Wichita Aircraft

Certification Office, 1801 Airport Road,

Mid-Continent Airport, Wichita, Kansas

67209; telephone (316) 946–4128;

facsimile (316) 946–4407.

SUPPLEMENTARY INFORMATION:

Events Leading to This AD

Recently, a Cessna Model 525

airplane was involved in an incident

where the left main landing gear (MLG)

collapsed during the landing roll even

though cockpit indications showed that

the MLG was in the normal down and

locked position. Investigation revealed

that loss of dry-film lubricant on the

MLG trunnion bearings caused this

incident.

Further investigation of the MLG of

Cessna Model 525 airplanes indicates

that this dry-film lubricant in the MLG

trunnion bearings becomes inadequate

over time. When these bearings are not

properly lubricated, the roll pin that

goes through the trunnion and bearing

shaft fails, which causes the pin to back

out of the bearing. This roll pin supports

the entire MLG, so its failure then

causes MLG collapse.

Applicable Service Information

Cessna has issued the following

service information:

• Cessna Alert Service Letter

SLA525–32–11, Revision 1, dated

October 1, 1996, which includes

procedures for inspecting the MLG

trunnion pins for proper installation;

and

• Cessna Service Bulletin SB525–32–

08, Revision 1, dated October 1, 1996,

which includes procedures for replacing

the existing dry-film lubricated MLG

trunnion slot bearings with sealed and

self-lubricating bearings.

The FAA’s Determination

After examining the circumstances

and reviewing all available information

related to the incident described above,

including the above-referenced service

information, the FAA has determined

that AD action should be taken to

prevent MLG collapse caused by

trunnion bearing failure, which could

result in loss of control of the airplane

during landing operations.

Explanation of the Provisions of This

AD

Since an unsafe condition has been

identified that is likely to exist or

develop in other Cessna Model 525

airplanes of the same type design, this

AD requires repetitively inspecting the

main landing gear (MLG) trunnion pins

for proper installation, and either

immediately or eventually replacing the

existing dry-film lubricated MLG

trunnion slot bearings with sealed and

self-lubricating bearings. Only two

inspections will be allowed before

mandatory replacement of the MLG

trunnion slot bearings. Accomplishment

of the inspections required by this AD

will be in accordance with Cessna Alert

Service Letter SLA525–32–11, Revision

1, dated October 1, 1996.

Accomplishment of the replacement

required by this AD will be in

accordance with Cessna Service Bulletin

SB525–32–08, Revision 1, dated October

1, 1996.

Determination of the Effective Date of

the AD

Since a situation exists (loss of control

of the airplane during landing

operations) that requires the immediate

adoption of this regulation, it is found

that notice and opportunity for public

prior 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 immediate flight safety and,

thus, was not preceded by notice and

opportunity to 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 should identify the

Rules Docket number and be submitted

in triplicate to the address specified

above. 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,