AD 2001-13-18 R1

The FAA is revising Airworthiness Directive (AD) 2001-13-18, which applies to Raytheon Aircraft Corporation (Raytheon) Beech Models 45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) airplanes. AD 2001-13-18 currently requires you to repetitively inspect the wing spar assembly for cracks and replace any wing spar assembly found cracked (unless the spar assembly has a crack indication in the filler strip where the direction of the crack is toward the outside edge of the filler strip). AD 2001-13-18 also requires you to report the results of the initial inspection and maintain the flight and operating restrictions required by AD 99-12-02 until the initial inspection is done. We approved alternative methods of compliance (AMOCs) to AD 2001-13-18. We have since determined that those AMOCs do not address all critical areas in the wing spar assemblies and should no longer be valid. We are issuing this revision to AD 2001-13-18 for the purpose of eliminating the AMOCs to AD 2001-13-18. The actions of this AD are intended to prevent wing spar failure caused by fatigue cracks in the wing spar assemblies and ensure the operational safety of the above-referenced airplanes.

Final rule; request for comments.

2001-13-18 R1 Raytheon Aircraft Company: Amendment 39-13496; Docket No. 2000-CE-09-AD; Revises AD 2001-13-18, Amendment 39-12300.

When Does This AD Become Effective?

(a) This AD becomes effective on March 15, 2004.

What Airplanes Are Affected by This AD?

(b) This AD applies to Beech Models 45 (YT-34), A45 (T-34A, B- 45), and D45 (T-34B) airplanes, all serial numbers, that are certificated in any category.

What Is the Unsafe Condition Presented in This AD?

(c) We are issuing this AD to detect and correct cracks in the wing spar assemblies and ensure the operational safety of the above- referenced airplanes.

What Must I Do To Address This Problem?

(d) To address this problem, you must maintain the actions of AD 99-12-02 that are outlined in paragraphs (d)(1), (d)(2), and (d)(3) of this AD, including all subparagraphs, until you accomplish the initial inspection required in paragraph (d)(5) of this AD (paragraphs (d)(1) through (d)(4) are actions retained from AD 99- 12-02, and paragraphs (d)(5) through (d)(7) are actions new to this AD):

Action
When
In accordance with
(1) Accomplish the following placard requirements:
(i) Fabricate two placards using letters of at least 1/10-inch in height with each consisting of the following words:
Never exceed speed, Vne-175 MPH (152 knots) IAS; Normal Acceleration (G) Limits -- 0, and +2.5; ACROBATIC MANEUVERS PROHIBITED.
(ii) Install these placards on the airplane instrument panels (one on the front panel and one on the rear panel) next to the airspeed indicators within the pilot s clear view.
(iii) Insert a copy of this AD into the Limitations Section of the Airplane Flight Manual (AFM).
All actions required prior to further flight after July 9, 1999 (the effective date of AD 99-12-02), unless already accomplished.
Not Applicable.
(2) Modify each airspeed indicator glass by accomplishing the following:
(i) Place a red radial line on each indicator glass at 175 miles per hour (mph) (152 knots).
(ii) Place a white slippage index mark between each airspeed indicator glass and case to visually verify that the glass has not rotated.
All actions required within 10 hours time-in-service (TIS) after July 9, 1999 (the effective date of AD 99-12-02), unless already accomplished.
Not Applicable.
(3) Mark the outside surface of the g meters with lines of approximately 1/16-inch by 3/16-inch, as follows:
(i) A red line at 0 and 2.5; and
(ii) A white slippage mark between each g meter glass and case to visually verify that the glass has not rotated.
All actions required within 10 hours time-in-service (TIS) after July 9, 1999 (the effective date of AD 99-12-02), unless already accomplished.
Not Applicable.
(4) The actions required by paragraphs (d)(1), (d)(2), and (d)(3) are no longer required after the initial inspection required in paragraph (d)(5) of this AD is accomplished.
Upon accomplishment of the initial inspection required in paragraph (d)(5) of this AD, unless already accomplished.
Raytheon Aircraft Mandatory Service Bulletin No. SB 57-3329, Issued: February, 2000.
(5) Inspect the wing spar assemblies for cracks
Initially inspect within the next 80 hours time-in-service (TIS) after August 16, 2001 (the effective date of AD 2001-13-18) or within 12 months after August 16, 2001 (the effective date of AD 2001-13-18), whichever occurs later, unless already accomplished. Inspect thereafter at intervals not to exceed
80 hours TIS.
Raytheon Aircraft Mandatory Service Bulletin No. SB 57-3329, Issued: February, 2000.

(6) Replace any cracked wing spar assembly. A crack indication in the filler strip is allowed if the direction of the crack is toward the out-side edge of the filler strip. If the direction of the crack is toward the inside edge of the filler strip or any crack is found in any other area, you must replace the cracked wing spar assembly.
Prior to further flight after the required inspection where the cracked wing spar assembly is found.
The applicable maintenance manual.
(7) Submit a report to FAA that describes the damage found on the wing spar. Use the chart on pages 58 through 60 of Raytheon Aircraft Mandatory Service Bulletin No. SB
57-3329, Issued: February, 2000.
(i) Submit this report even if no cracks are found.
(ii) Submit this report to FAA at the address found in paragraph (g) of this AD.
Within 10 days after the initial inspection or within 10 days after August 16, 2001 (the effective date of AD 2001-13-18), which-ever occurs later, unless already accomplished.
Pages 58 through 60 of Raytheon Aircraft Mandatory Service Bulletin No. SB 57-3329, Issued: February, 2000.

Are Any Other ADs Affected by This Action?

(e) This AD revises AD 2001-13-18, Amendment 39-12300.

What About Alternative Methods of Compliance?

(f) As of March 15, 2004 (the effective date of this AD), all alternative methods of compliance approved under AD 2001-13-18 are not approved for this AD and are no longer valid. Any alternative method of compliance must reference "AD 2001-13-18 R1" in order to be valid.

(g) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Wichita Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance for this AD, contact Paul Nguyen, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4125; facsimile: (316) 946-4107.

Does This AD Incorporate Any Material by Reference?

(h) You must do the actions required by this AD following the instructions in Raytheon Aircraft Mandatory Service Bulletin No. SB 57-3329, Issued: February, 2000. On August 16, 2001 (66 FR 34802, July 2, 2001), the Director of the Federal Register previously approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You may get a copy from Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085; telephone: (800) 625-7043 or (316) 676-4556. You may review copies at FAA, Central Region, Office of the Regional Counsel, 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.

Has FAA Taken Any Action to This Point?

In-flight separation of the right wing on a Raytheon Beech Model A45 (T34A) airplane caused FAA to issue AD 99-12-02, Amendment 39-11193 (64 FR 31689, June 14, 1999) against Raytheon Beech Models 45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) airplanes. This AD requires:

--Incorporating flight and operating limitations that restrict the airplanes to normal category operation and prohibit them from acrobatic and utility category operations;
--Limiting the flight load factor to 0 to 2.5 G; and
--Limiting the maximum airspeed to 175 miles per hour (mph) (152 knots).

AD 99-12-02 was issued as an interim action until the development of FAA-approved inspection procedures.
Those procedures were developed and FAA superseded AD 99-12-12 with AD 2001-13-18, Amendment 39-12300 (66 FR 34802, July 2, 2001). AD 2001- 13-18 contains the following provisions:

--Requires you to repetitively inspect the wing spar assemblies for cracks and replace any cracked wing spar assembly. A crack indication in the filler strip is allowed if the direction of the crack is toward the outside edge of the filler strip;
--Requires you to report the results of the initial inspection;
--Requires you to maintain the flight and operating restrictions that AD 99-12-02 currently requires until you do the initial inspection and possible replacement specified in this AD; and
--Allows you to change the flight and operating restrictions that AD 99-12-02 currently requires after the wing spar assemblies are inspected and the wing spar assembly either is replaced, is crack free, or only has a crack indication in the filler strip where the direction of the crack is toward the outside of the filler strip.

You are required to do the inspections of AD 2001-13-18 following the procedures of Raytheon Mandatory Service Bulletin No. SB 57-3329, Issued: February, 2000.

What Has Happened Since AD 2001-13-18 ToInitiate This AD Action?

In November 2003, a Raytheon Beech Model A45 (T34A) airplane crashed after the right wing failed at Wing Station (WS) 34 on the forward spar and WS 66.00 on the rear spar. AD 2001-13-18 was established to inspect the wing spar assemblies at four locations:

1. Nine fasteners at the WS 34 forward spar.

2. The lower rear bathtub fitting.

3. One fastener at WS 64 on the forward spar.

4. Two fasteners at WS 66.00 on the rear spar.

The FAA has approved and issued different alternative methods of compliance (AMOCs) for the inspections of AD 2001-13-18. These AMOCs consist of a combination of modifications and inspections to address the condition.

None of the AMOCs issued under AD 2001-13-18 address all four locations of the wing spar assemblies.

FAA's Determination and Requirements of This AD

What Has FAA Decided?

We have evaluated all pertinent information including all information from the November 2003 accident and determined that the AMOCs approved under AD 2001-13-18 do not address all critical areas in the wing spar assemblies and should no longer be valid in order to prevent wing spar failure caused by fatigue cracks in the wing spar assemblies and ensure the operational safety of the above-referenced airplanes.

Therefore, we have determined that AD 2001-13-18 should be revised for the purpose of eliminating the AMOCs to AD 2001-13-18.

What Does This AD Require?

This AD revises AD 2001-13-18 by retaining all actions (including compliance times) of AD 2001-13-18, but not retaining the AMOCs approved through that AD. The requirements of the actual AD portion of AD 2001-13-18 will remain the same.

In preparing this rule, we contacted type clubs and aircraft operators to get technical information and information on operational and economic impacts. We did not receive any information through these contacts. If received, we would have included a discussion of any information that may have influenced this action in the rulemaking docket.

How Does the Revision to 14 CFR Part 39 Affect This AD?

On July 10, 2002, we published a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), which governs FAA's AD system. This regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance. This material previously was included in each individual AD. Since this material is included in 14 CFR part 39, we will not include it in future AD actions.

Comments Invited

Will I Have the Opportunity To Comment Before You Issue the Rule?

This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include "AD Docket No. 2000-CE-09-AD" in the subject line of yourcomments. If you want us to acknowledge receipt of your mailed comments, send us a self-addressed, stamped postcard with the docket number written on it; we will date-stamp your postcard and mail it back to you. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify it. If a person contacts us through a nonwritten communication, and that contact relates to a substantive part of this AD, we will summarize the contact and place the summary in the docket. We will consider all comments received by the closing date and may amend the AD in light of those comments.

Regulatory Findings

Will This AD Impact Various Entities?

We have determined that this AD will not have federalism implications under Executive Order 13132. This AD 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 andresponsibilities among the various levels of government.

Will This AD Involve a Significant Rule or Regulatory Action?

For the reasons discussed above, I certify that this AD:

1. Is not a "significant regulatory action" under Executive Order 12866;

2. Is not a "significant rule" under the 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.

We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include "AD Docket No. 2000-CE-09-AD" in your request.

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. The FAA amends 39.13 by removing Airworthiness Directive (AD) 2001-13-18, Amendment 39-12300 (66 FR 34802, July 2, 2001), and by adding a new AD to read as follows: