Federal Register / Vol. 66, No. 242 / Monday, December 17, 2001 / Proposed Rules 64925

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–CE–42–AD]

RIN 2120–AA64

Airworthiness Directives; Cessna

Aircraft Company P206, TP206, TU206,

U206, 207, T207, 210, P210, and T210

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to certain Cessna

Aircraft Company (Cessna) P206, TP206,

TU206, U206, 207, T207, 210, P210, and

T210 series airplanes. This proposed AD

would require you to visually inspect

certain horizontal stabilizer attachment

reinforcement brackets for the existence

of seam welds and replace any

reinforcement bracket found without

seam welds. This proposed AD

authorizes the pilot to check the

logbooks to determine whether one of

the affected horizontal stabilizer

attachment reinforcement brackets is

installed. This proposed AD is the result

of a report that certain parts were

manufactured without seam welds. The

actions specified by this proposed AD

are intended to detect and replace

structurally deficient horizontal

stabilizer attachment brackets.

Continued use of such brackets could

result in structural failure of the

horizontal stabilizer with reduced or

loss of control of the airplane.

DATES: The Federal Aviation

Administration (FAA) must receive any

comments on this proposed rule on or

before February 11, 2002.

ADDRESSES: Submit comments to FAA,

Central Region, Office of the Regional

Counsel, Attention: Rules Docket No.

2001–CE–42–AD, 901 Locust, Room

506, Kansas City, Missouri 64106. You

may view any comments at this location

between 8 a.m. and 4 p.m., Monday

through Friday, except Federal holidays.

You may get service information that

applies to this proposed AD from

Cessna Aircraft Company, Product

Support, P.O. Box 7706, Wichita,

Kansas 67277; telephone: (316) 517–

5800; facsimile: (316) 942–9006. You

may also view this information at the

Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Al

Phillips, Aerospace Engineer, Wichita

Aircraft Certification Office, FAA, 1801

Airport Road, Mid-Continent Airport,

Wichita, Kansas 67209; telephone: (316)

946–4116; facsimile: (316) 946–4407.

SUPPLEMENTARY INFORMATION:

Comments Invited

How Do I Comment on This Proposed

AD?

The FAA invites comments on this

proposed rule. You may submit

whatever written data, views, or

arguments you choose. You need to

include the rule’s docket number and

submit your comments to the address

specified under the caption ADDRESSES.

We will consider all comments received

on or before the closing date. We may

amend this proposed rule in light of

comments received. Factual information

that supports your ideas and suggestions

is extremely helpful in evaluating the

effectiveness of this proposed AD action

and determining whether we need to

take additional rulemaking action.

Are There Any Specific Portions of This

Proposed AD I Should Pay Attention to?

The FAA specifically invites

comments on the overall regulatory,

economic, environmental, and energy

aspects of this proposed rule that might

suggest a need to modify the rule.

You may view all comments we

receive before and after the closing date

of the rule in the Rules Docket. We will

file a report in the Rules Docket that

summarizes each contact we have with

the public that concerns the substantive

parts of this proposed AD.

How Can I Be Sure FAA Receives My

Comment?

If you want FAA to acknowledge the

receipt of your comments, you must

include a self-addressed, stamped

postcard. On the postcard, write

‘‘Comments to Docket No. 2001–CE–42–

AD.’’ We will date stamp and mail the

postcard back to you.

Discussion

What Events Have Caused This

Proposed AD?

Cessna notified FAA of a defect in the

manufacturing of the horizontal

stabilizer attachment reinforcement

brackets. Cessna manufactured

reinforcement brackets without seam

welds on certain Cessna Model 206H

and T206H airplanes. AD 2001–09–06,

Amendment 39–12211, (66 FR 21278,

April 30. 2001), addresses these

airplanes. The seam welds help provide

the required structural integrity for the

horizontal stabilizer attachment bracket.

Since the issuance of AD 2001–09–06,

Cessna determined that certain Model

P206, TP206, TU206, U206, 207, T207,

210, P210, and T210 series airplanes

may have had horizontal stabilizer

attachment reinforcement brackets (part

number 1232624–1) without seam welds

installed as replacement parts. Cessna

shipped these brackets from February

27, 1998, through March 17, 2000.

What Are the Consequences if the

Condition Is Not Corrected?

This condition, if not corrected, could

result in structural failure of the

horizontal stabilizer with reduced or

loss of control of the airplane.

Is There Service Information That

Applies to This Subject?

Cessna has issued Service Bulletin

SEB00–10, dated November 6, 2000.

What Are the Provisions of This Service

Information?

The service bulletin includes

procedures for:

—Visually inspecting the right and left

horizontal stabilizer attachment

reinforcement brackets for the

existence of seam welds along the

lower inboard and outboard wall/

flange; and

—Removing and replacing the

horizontal stabilizer assemblies with

new parts.

The FAA’s Determination and an

Explanation of the Provisions of This

Proposed AD

What Has FAA Decided?

After examining the circumstances

and reviewing all available information

related to the incidents described above,

we have determined that:

—The unsafe condition referenced in

this document exists or could develop

on other Cessna P206, TP206, TU206,

U206, 207, T207, 210, P210, and T210

series airplanes of the same type

design;

—The actions specified in the

previously-referenced service

information should be accomplished

on the affected airplanes; and

—AD action should be taken in order to

correct this unsafe condition.

What Would This Proposed AD Require?

This proposed AD would require you

to incorporate the actions in the

previously-referenced service bulletin.

What Are the Differences Between the

Service Information and This Proposed

AD?

Cessna requires you to inspect and, if

necessary, replace the horizontal

stabilizer attachment reinforcement

brackets, part number 1232624–1,

within 20 hours time-in-service (TIS),

64926 Federal Register / Vol. 66, No. 242 / Monday, December 17, 2001 / Proposed Rules

not to exceed 30 days, of operation. We

are proposing a requirement that you

inspect and, if necessary, replace the

horizontal stabilizer attachment

reinforcement brackets, part number

1232624–1, within 50 hours TIS of

operation after the effective date of the

proposed AD.

We do not have justification to require

this action within 20 hours TIS.

Compliance times such as this are

utilized when we have identified an

urgent safety of flight situation. We

believe that 50 hours TIS will give the

owners/operators of the affected

airplanes enough time to have the

proposed actions accomplished without

compromising the safety of the

airplanes.

Cost Impact

How Many Airplanes Would This

Proposed AD Impact?

We estimate that this proposed AD

affects 144 airplanes in the U.S. registry.

What Would Be the Cost Impact of This

Proposed AD on Owners/Operators of

the Affected Airplanes?

We estimate the following costs to

accomplish the proposed inspection:

Labor cost Parts cost Total cost

per airplane Total cost on U.S. operators

2 workhours × $60 = $120 ....................... Not applicable ........................................... $120 $120 × 144 = $17,280.

We estimate the following costs to accomplish any necessary replacements that would be required based on the

results of the proposed inspection. We have no way of determining the number of airplanes that may need such

replacement:

Labor cost Parts cost Total cost per airplane

24 workhours to replace both brackets × $60 =

$1,440.

$135 for both the right and left bracket ........... $1,440 + $135 = $1,575.

Regulatory Impact

Would This Proposed AD Impact

Various Entities?

The regulations proposed herein

would 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 proposed rule

would not have federalism implications

under Executive Order 13132.

Would This Proposed AD Involve a

Significant Rule or Regulatory Action?

For the reasons discussed above, I

certify that this proposed 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) if

promulgated, 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 draft

regulatory evaluation prepared for this

action has been placed 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, Safety.

The Proposed Amendment

Accordingly, under the authority

delegated to me by the Administrator,

the Federal Aviation Administration

proposes to amend 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 airworthiness directive (AD) to

read as follows:

Cessna Aircraft Company: Docket No. 2001–

CE–42–AD

(a) What airplanes are affected by this AD?

This AD affects the following airplane

models and serial numbers that are

certificated in any category:

Model Serial Nos.

P206C and TP206C ................................................................................. P206–0420 through P206–0519.

P206D and TP206D ................................................................................. P206–0520 through P206–0603.

P206E and TP206E .................................................................................. P20600604 through P20600647, and P206–0001.

U206C and TU206C ................................................................................. U206–0915 through U206–1234.

U206D and TU206D ................................................................................. U206–1235 through U206–1444, U20601445 through U20601587.

U206E and TU206E ................................................................................. U20601588 through U20601700.

U206F and TU206F .................................................................................. U20601701 through U20602588, and U20602590 through U20603521.

U206G and TU206G ................................................................................ 676, U20602589, and U20603522 through U20607020.

207 and T207 ........................................................................................... 20700001 through 20700362.

207A and T207A ...................................................................................... 20700363 through 20700788.

210G ......................................................................................................... 21058819 through 21058936.

210H ......................................................................................................... 21058937 through 21059061.

210J .......................................................................................................... 21059062 through 21059199.

210K and T210K ...................................................................................... 21059200 through 21059502.

210L and T210L ....................................................................................... 21059503 through 21061041, and 21061043 through 21061573.

210M and T210M ..................................................................................... 21061042, and 21061574 through 21062954.

210N and T210N ...................................................................................... 21062955 through 21064897.

P210N ....................................................................................................... P21000001 through P21000834.

T210G ....................................................................................................... T210–0198 through T210–0307.

Federal Register / Vol. 66, No. 242 / Monday, December 17, 2001 / Proposed Rules 64927

Model Serial Nos.

T210H ....................................................................................................... T210–0308 through T210–0392.

T210J ........................................................................................................ T210–0393 through T210–0454, and 21058140.

(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 replace structurally deficient

horizontal stabilizer attachment brackets.

Continued use of such brackets could result

in structural failure of the horizontal

stabilizer with reduced or loss of control of

the airplane.

(d) What actions must I accomplish to

address this problem? To address this

problem, you must accomplish the following:

Actions Compliance Procedures

(1) Maintenance Records Check:

(i) Check the maintenance records to determine whether a horizontal stabilizer

attachment reinforcement bracket, part

number (P/N) 1232624–1 shipped by

Cessna from February 27, 1998,

through March 17, 2000, is installed.

The owner/operator holding at least a

private pilot certificate as authorized by

section 43.7 of the Federal Aviation

Regulations (14 CFR 43.7) may perform

this check.

Within the next 50 hours time-in-service (TIS)

after the effective date of this AD, unless already accomplished.

No special procedures required to check the

logbook.

(ii) If, by checking the maintenance

records, the owner/operator can positively show that a horizontal stabilizer

attachment reinforcement bracket, P/N

1232624–1 shipped by Cessna from

February 27, 1998, through March 17,

2000, is not installed, then the inspection requirement of paragraph (d)(2) and

the replacement requirement of paragraph (d)(3) of this AD does not apply.

You must make an entry into the aircraft

records that shows compliance with this

portion of the AD, in accordance with

section 43.9 of the Federal Aviation

Regulations (14 CFR 43.9).

(2) Inspection:

Visually inspect the right and left horizontal stabilizer attachment reinforcement brackets, part number (P/N)

1232624–1, for the existence of seam

welds along both the lower inboard and

outboard wall/flange.

Within the next 50 hours TIS after the effective date of this AD, unless already accomplished.In accordance with the Accomplishment Instructions in Cessna Service Bulletin

SEB00–10, dated November 6, 2000, and

the applicable maintenance manual.

(3) Replacement:

(i) If no seam weld is found along both the

lower inboard and outboard wall/flange

on the right and left horizontal stabilizer

attachment reinforcement bracket during

the inspection required in paragraph

(d)(2) of this AD, replace with a new or

airworthy P/N 1232624–1 horizontal stabilizer attachment reinforcement bracket.

Accomplish any necessary replacements prior

to further flight after the inspection required

by this AD, unless already accomplished.

In accordance with the Accomplishment Instructions in Cessna Service Bulletin

SEB00–10, dated November 6, 2000, and

the applicable maintenance manual.

(ii) If the right and left horizontal stabilizer

attachment reinforcement bracket has

seam welds along both the lower inboard and outboard wall/flange, no further action is required.

(4) Installation Prohibition:

Do not install any P/N 1232624–1 horizontal

stabilizer attachment reinforcement bracket (or FAA-approved equivalent part) unless the bracket:

Not applicable ................................................... Not applicable.

(i) is inspected as required in paragraph

(d)(2) of this AD; and

(ii) has seam welds along both the lower

inboard and outboard wall/flange

64928 Federal Register / Vol. 66, No. 242 / Monday, December 17, 2001 / Proposed Rules

(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, Wichita 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, Wichita ACO.

Note: 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.

(f) Where can I get information about any

already-approved alternative methods of

compliance? Contact Al Phillips, Aerospace

Engineer, Wichita Aircraft Certification

Office, FAA, 1801 Airport Road, MidContinent Airport, Wichita, Kansas 67209;

telephone: (316) 946–4116; facsimile: (316)

946–4407.

(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) How do I get copies of the documents

referenced in this AD? You may get copies of

the documents referenced in this AD from

Cessna Aircraft Company, Product Support,

P.O. Box 7706, Wichita, Kansas 67277. You

may view these documents at FAA, Central

Region, Office of the Regional Counsel, 901

Locust, Room 506, Kansas City, Missouri

64106.

Issued in Kansas City, Missouri, on

December 6, 2001.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 01–30954 Filed 12–14–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–CE–41–AD]

RIN 2120–AA64

Airworthiness Directives; SOCATA—

Groupe Aerospatiale Models MS 892A–

150, MS 892E–150, MS 893A, MS 893E,

MS 894A, MS 894E, Rallye 150T, and

Rallye 150ST Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

supersede Airworthiness Directive (AD)

77–15–06, which applies to all

SOCATA—Groupe Aerospatiale (Socata)

Models MS 892A–150, MS 892E–150,

MS 893A, MS 893E, Rallye 150T, and

Rallye 150ST airplanes. AD 77–15–06

currently requires you to repetitively

inspect the engine mount assembly for

cracks, repair any cracks found, and

modify the brackets on airplanes with

right angle engine mounts. This

proposed AD is the result of the French

airworthiness authority’s determination

that updated service information and

additional aircraft should be added to

the applicability of AD 77–15–06. This

proposed AD would retain the

inspection and repair requirements of

the current AD and would add the

information communicated by the

French airworthiness authority. The

actions specified by this proposed AD

are intended to detect and correct cracks

in the engine mount assembly. Such a

condition could cause the engine mount

assembly to fail, which could result in

loss of control of the airplane.

DATES: The Federal Aviation

Administration (FAA) must receive any

comments on this rule on or before

January 11, 2002.

ADDRESSES: Submit comments to FAA,

Central Region, Office of the Regional

Counsel, Attention: Rules Docket No.

2001–CE–41–AD, 901 Locust, Room

506, Kansas City, Missouri 64106. You

may view any comments at this location

between 8 a.m. and 4 p.m., Monday

through Friday, except Federal holidays.

You may get service information that

applies to this proposed AD from

SOCATA Groupe Aerospatiale,

Customer Support, Aerodrome TarbesOssun-Lourdes, BP 930—F65009 Tarbes

Cedex, France; telephone: 011 33 5 62

41 73 00; facsimile: 011 33 5 62 41 76

54; or the Product Support Manager,

SOCATA—Groupe Aerospatiale, North

Perry Airport, 7501 Pembroke Road,

Pembroke Pines, Florida 33023;

telephone: (954) 894–1160; facsimile:

(954) 964–4191. You may also view this

information at the Rules Docket at the

address above.

FOR FURTHER INFORMATION CONTACT: Karl

Schletzbaum, Aerospace Engineer, FAA,

Small Airplane Directorate, 901 Locust,

Room 301, Kansas City, Missouri 64106;

telephone: (816) 329–4146; facsimile:

(816) 329–4090.

SUPPLEMENTARY INFORMATION:

Comments Invited

How do I comment on this proposed

AD? The FAA invites comments on this

proposed rule. You may submit

whatever written data, views, or

arguments you choose. You need to

include the rule’s docket number and

submit your comments to the address

specified under the caption ADDRESSES.

We will consider all comments received

on or before the closing date. We may

amend this proposed rule in light of

comments received. Factual information

that supports your ideas and suggestions

is extremely helpful in evaluating the

effectiveness of this proposed AD action

and determining whether we need to

take additional rulemaking action.

Are there any specific portions of this

proposed AD I should pay attention to?

The FAA specifically invites comments

on the overall regulatory, economic,

environmental, and energy aspects of

this proposed rule that might suggest a

need to modify the rule. You may view

all comments we receive before and

after the closing date of the rule in the

Rules Docket. We will file a report in

the Rules Docket that summarizes each

contact we have with the public that

concerns the substantive parts of this

proposed AD.

How can I be sure FAA receives my

comment? If you want FAA to

acknowledge the receipt of your

comments, you must include a selfaddressed, stamped postcard. On the

postcard, write ‘‘Comments to Docket

No. 2001–CE–41–AD.’’ We will date

stamp and mail the postcard back to

you.

Discussion

Has FAA taken any action to this

point? Fatigue cracks found on the

engine mount assemblies of Socata

Models MS 892A–150, MS 892E–150,

MS 893A, MS 893E, Rallye 150T, and

Rallye 150ST airplanes caused us to

issue AD 77–15–06, Amendment 39–

2975. This AD currently requires the

following:

—Inspecting the engine mount assembly

for cracks at repetitive intervals;