ADs updated daily at www.tdatacorp.com (preamble attached)

2001-23-10 Raytheon Aircraft Company: Amendment 39-12507;
Docket No. 2001-CE-35-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:

(1) Group 1: Raytheon may have installed the affected flap flex shaft

assemblies on the following airplanes at manufacture:

Models Serial Nos.

(i) A36 E-3302 through E-3398

(ii) B36TC EA-652 through EA-677

(iii) 58 TH-1936 through TH-1988

and TH-1990 through

TH-1996.

(2) Group 2: The affected flap flex shaft assemblies and flap

actuator assembly could be installed through spare replacement on any

of the following model airplanes:

Models Serial Nos.

(i) 35-33, 35-A33, 35-B33, All serial numbers

35-C33, 35-C33A, E33,

E33A, E33C, F33, F33A,

F33C, and G33.

(ii) T-34C, T-34C (T-34C-1), All serial numbers.

T-34C(34C), A45 (T-34A, B-45),

D45 (T-34B), and 45 (YT-34).

(iii) 35, 35R, A35, B35, C35, D35, All serial numbers except

E35, F35, G35, H35, J35, D-1 through D-837.

K35, M35, N35, P35, S35, V35,

V35A, and V35B.

(iv) 36, A36, A36TC, and B36TC All serial numbers except

E-3302 through E-3398 and

EA-652 through EA-677

(those serial numbers are

included in Group 1).

(v) 95-55, 95-A55, 95-B5 5, All serial numbers.

95-B55A, 95-B55B (T-42A),

95-C55, 95-C55A D55, D55A,

E55, and E55A.

(vi) 56TC and A56TC All serial numbers.

(vii) 58, 58A, 58P, 58PA, All serial numbers except

58TC, and 58TCA. TH-1936 through TH-1988 and

TH-1900 through TH-1996

(those serial numbers are

included in Group 1)

(viii) 95, B95, B95A, D95A, and E95 All serial numbers.

(b) Who must comply with this AD? Anyone who wishes to operate any of

the above airplanes must comply with this AD.

AD are intended to prevent separation of the flap flex shaft assembly

caused by improper heat treatment. Such a condition could lead to an

asymmetric flap condition, which could result in uncommanded roll of

the airplane.

(d) What actions must I accomplish to address this problem for Group

1 airplanes? To address this problem for Group 1 airplanes, you must

accomplish the following:

GROUP 1 AIRPLANES:

ACTIONS:

(1) Inspect the identification label on the left-hand (LH) flap flex

shaft assembly, part (P/N) 12527Y-63.31, and the number right-hand

(RH) flap flex shaft assembly, P/N 12163Y-63.31 or 12163Y-1, to

determine the manufacture date. If the manufacture date on the

identification label on any of the flex flap shaft assemblies is

before January 2000 and after April 2001, the flap flex assemblies

are not affected and do not need to be replaced.

COMPLIANCE:

Within the next 25 hours time-in- service (TIS) after December 13,

2001, the effective date of this AD.

PROCEDURES:

In accordance with Raytheon Mandatory Service Bulletin SB27-3478,

Issued: September 2001, and the applicable maintenance manual.

ACTIONS:

(2) If the manufacture date on the identification label on any of the

flex flap shaft assemblies is from January 2000 through April 2001,

replace with parts that were manufactured before January 2000 and

after April 2001.

COMPLIANCE:

Prior to further flight after the inspection required in paragraph

(d)(1) of this AD.

PROCEDURES:

In accordance with Raytheon Mandatory Service Bulletin SB27-3478,

Issued: September 2001, and the applicable maintenance manual.

ACTIONS:

(3) Do not install on any airplane, a LH flap flex shaft assembly,

P/N 12527Y-63.31, a RH flap flex shaft assembly, P/N 12163Y-63.31 or

12163Y-1, or a flap actuator assembly, P/N 45-521212 (any dash number

containing a flap flexible shaft assembly), that has a manufacture

date from January 2000 through April 2001.

COMPLIANCE:

As of December 13, 2001, the effective date of this AD.

PROCEDURES:

In accordance with Raytheon Mandatory Service Bulletin SB27-3478,

Issued: September 2001.

(e) What actions must I accomplish to address this problem for Group

2 airplanes? To address this problem for Group 2 airplanes, you must

accomplish the following:

GROUP 2 AIRPLANES:

ACTIONS:

(1) Check the airplane logbook to determine whether the LH flap flex

shaft assembly, P/N 12527Y-63.31, the RH flap flex shaft assembly,

P/N 12163Y-63.31 or 12163Y-1, or the flap actuator assembly, P/N 45-

521212 (any dash number), has been replaced since March 1, 2000.

(i) 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 check the airplane logbook.

(ii) If, by checking the airplane logbook, the pilot can positively

show that the LH or the RH flap flex shaft assembly or the flap

actuator assembly has never been replaced since March 1, 2000, no

further action is required..

COMPLIANCE:

Within the next 25 hours time-in- service (TIS) after December 13,

2001, the effective date of this AD.

PROCEDURES:

In accordance with Raytheon Mandatory Service Bulletin SB27-3478,

Issued: September 2001.

ACTIONS:

(2) If the check of the airplane logbook shows that the LH or the RH

flap flex shaft assembly or the flap actuator assembly has been

replaced since March 1, 2000, or if complete records of the LH and RH

flap flex assembly or the flap actuator assembly do not exist,

inspect the identification labels on the flap flex shaft assemblies

to determine the manufacture date.

(i) If the manufacture date on the identification label on any of the

flex flap shaft assemblies is from January 2000 through April 2001,

replace with parts that were manufactured before January 2000 and

after April 2001.

(ii) If the manufacture date on any identification label is before

January 2000 and after April 2001, the flap flex assemblies are not

affected and do not need to be replaced.

COMPLIANCE:

Within the next 25 hours time-in- service (TIS) after December 13,

2001, the effective date of this AD. Accomplish replacements prior to

further flight.

PROCEDURES:

In accordance with Raytheon Mandatory Service Bulletin SB27-3478,

Issued: September 2001, and the applicable maintenance manual

ACTIONS:

(3) Do not install on any airplane, a LH flap flex shaft assembly,

P/N 12527Y- 63.31, a RH flap flex shaft assembly, P/N 12163Y-63.31 or

12163Y-1, or a flap actuator assembly, P/N 45- 531212 (any dash

number containing a flap flexible shaft assembly), that has a

manufacture date from January 2000 through April 2001.

COMPLIANCE:

As of December 13, 2001, the effective date of this AD.

PROCEDURES:

In accordance with Raytheon Mandatory Service Bulletin SB27-3478,

Issued: September 2001.

(f) 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 (f) 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.

(g) Where can I get information about any already-approved

alternative methods of compliance? Contact Paul DeVore, Aerospace

Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport

Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316)

946-4142; facsimile: (316) 946-4407.

(h) 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. You must adhere to

the limitations presented in the appendix to this AD.

(i) Are any service bulletins incorporated into this AD by reference?

Actions required by this AD must be done in accordance with Raytheon

Mandatory Service Bulletin SB 27-3478, Issued: September 2001. 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 Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-

0085; telephone: (800) 429-5372 or (316) 676-3140. You may view this

information at 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.

(j) When does this amendment become effective? This amendment becomes

effective on December 13, 2001.

************* Appendix to Docket No. 2001-CE-35-AD *************

The following must be adhered to in order to obtain a special flight

permit as specified in paragraph (h).

Limitations--Flaps must be retracted for all takeoffs.

Emergency Procedures

Asymmetrical Flaps

Attempt to retract the flaps. If flaps will not retract, the airplane

will have a tendency to roll in the direction of the retracted flap.

This roll tendency will increase with increasing speed. Use aileron

trim and reduce speed as required to reduce roll forces.

Flaps-Up or Asymmetrical-Flap Landing

Follow all published Before Landing Procedures except for airspeed.

Maintain the published Flaps-Up Approach Speed. If this speed is not

published, use one of the following:

(a) Multiply the highest indicated flaps-up stall speed, found in the

Performance Section, by 1.3.

(b) For Bonanza Series, T-34A, T-34B, and 45, add 10 knots to the

published Flaps-Down Landing Approach Speed.

Landing Approach speed.

Plan on longer landing distance.

Issued in Kansas City, Missouri, on November 13, 2001.

James E. Jackson, Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: Paul DeVore, Aerospace Engineer,

FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-

Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4142;

facsimile: (316) 946-4407.

PREAMBLE TO THIS AD *************************************************

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-CE-35-AD; Amendment 39-12507; AD 2001-23-10]

RIN 2120-AA64

Airworthiness Directives; Raytheon Aircraft Company 33, T-34, 35, 36,

55, 56, 58, and 95 Series 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 Raytheon Aircraft Company (Raytheon) 33, T-

34, 35, 36, 55, 56, 58, and 95 Series airplanes. This AD requires you

to inspect the left-hand and right-hand flap flex shaft assemblies to

determine the manufacture date. This AD also requires you to replace

any flap flex shaft assemblies manufactured from January 2000 through

April 2001. This AD is the result four separate reports of flap drive

cable separation. The actions specified by this AD are intended to

prevent separation of the flap flex shaft assembly caused by improper

heat treatment. Such a condition could lead to an asymmetric flap

condition, resulting in uncommanded roll of the airplane.

DATES: This AD becomes effective on December 13, 2001.

The Director of the Federal Register approved the incorporation by

reference of certain publications listed in the regulation as of

December 13, 2001.

The Federal Aviation Administration (FAA) must receive any comments

on this rule on or before January 12, 2002.

ADDRESSES: Submit comments to FAA, Central Region, Office of the

Regional Counsel, Attention: Rules Docket No. 2001-CE-35-AD, 901

Locust, Room 506, Kansas City, Missouri 64106.

You may get the service information referenced in this AD from

Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085;

telephone: (800) 429-5372 or (316) 676-3140. You may view this

information at FAA, Central Region, Office of the Regional Counsel,

Attention: Rules Docket No. 2001-CE-35-AD, 901 Locust, Room 506,

Kansas City, Missouri 64106; or at the Office of the Federal

FOR FURTHER INFORMATION CONTACT: Paul DeVore, Aerospace Engineer,

FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-

Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4142;

facsimile: (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Discussion

What events have caused this AD? Raytheon has notified FAA of four

separate incidents of the flap drive cable separating on Models A36,

B36TC, and 58 airplanes. Three of the incidents occurred during

flight and resulted in asymmetric flap conditions. In all three

cases, a safe landing was made. The flap flex shaft failed on one

airplane while rigging the flaps on the ground.

Raytheon and FAA investigated the incidents and determined the cause

to be a result of a quality control problem. During manufacturing

from January 2000 through April 2001, the end of the flap flex shaft

assemblies was not being properly heat-treated. Improper heat-

treatment allowed the cable end to crack and separate from the flap

flex shaft assembly.

Information on the affected parts follows:

--The affected parts are part number 12527Y-63.31 (left-hand) flap

flex shaft assemblies, part number 12163Y-63.31 or 12163Y-1 (right-

hand) flap flex shaft assemblies, and part number 45-521212 (any dash

number) flap actuator assemblies, that were manufactured from January

2000 through April 2001. Raytheon has installed these parts on

certain Models A36, B36TC, and 58 airplanes at manufacture; and

--These flap flex shaft assemblies could be installed through spare

replacements on any of the following series airplanes: 33, T-34, 35,

36, 55, 56, 58, and 95. Specific models are listed in paragraph

(a)(1) and (a)(2) of this AD.

What are the consequences if the condition is not corrected? If this

condition is not corrected, separation of the flex flap shaft

assembly could result. Such a condition could lead to an asymmetric

flap condition, resulting in uncommanded roll of the airplane.

Is there service information that applies to this subject? Raytheon

has issued Mandatory Service Bulletin SB 27-3478, September 2001.

What are the provisions of this service information? The service

bulletin includes procedures for:

--Inspecting the left-hand flap flex shaft assembly, part number

12527Y-63.31 and the right-hand flap flex shaft assembly, part number

12163Y-63.31 or 12163Y-1, to determine the manufacture date;

--Replacing any flap flex shaft assembly manufactured from January

2000 through April 2001; and

--Inspecting the airplane logbook for airplanes with spare

replacement only, to see if any flap flex shaft assemblies or flap

actuator assemblies have been replaced since March 1, 2000, to

determine if the flap flex shaft assemblies need to be inspected and

possibly replaced.

The FAA's Determination and an Explanation of the Provisions of This

What has FAA decided? The FAA has reviewed all available information,

including the service information referenced above; and determined

that:

--The unsafe condition referenced in this document exists or could

develop on other Raytheon 33, T-34, 35, 36, 55, 56, 58, and 95 Series

airplanes of the same type design;

--The actions specified in the previously-referenced service

information (as specified in this AD) should be accomplished on the

affected airplanes; and

--AD action should be taken in order to correct this unsafe

condition.

What does this AD require? This AD requires you to incorporate the

actions in the previously-referenced service bulletin.

In preparation of this rule, we contacted type clubs and aircraft

operators to obtain technical information and information on

operational and economic impacts. We have included, in the rulemaking

docket, a discussion of information that may have influenced this

action.

Will I have the opportunity to comment prior to the issuance of the

rule? Because the unsafe condition described in this document could

result in separation of the flap flex shaft assembly which could lead

to an asymmetric flap condition, resulting in uncommanded roll of the

airplane, we find that notice and opportunity for public prior

comment are impracticable. Therefore, good cause exists for making

this amendment effective in less than 30 days.

Comments Invited

How do I comment on this AD? Although this action is in the form of a

final rule and was not preceded by notice and opportunity for public

comment, FAA invites your comments on the 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 specified above. We

may amend this rule in light of comments received. Factual

information that supports your ideas and suggestions is extremely

helpful in evaluating the effectiveness of the AD action and

determining whether we need to take additional rulemaking action.

Are there any specific portions of the AD I should pay attention to?

We specifically invite comments on the overall regulatory, economic,

environmental, and energy aspects of the 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 FAA contact

with the public that concerns the substantive parts of this AD.

How can I be sure FAA receives my comment? If you want us 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-35-AD.'' We will date stamp and mail the postcard

back to you.

Regulatory Impact

Does this AD impact various entities? These regulations 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, FAA has determined that this final rule

does not have federalism implications under Executive Order 13132.

Does this AD involve a significant rule or regulatory action? We have

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 (otherwise, an evaluation is

not required). A copy of it, if filed, may be obtained from the Rules

Docket.

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.

Sec. 39.13 [Amended]

2. FAA amends Sec. 39.13 by adding a new airworthiness directive (AD)

to read as follows: