Airworthiness directives: Raytheon,

[Federal Register: July 11, 2001 (Volume 66, Number 133)]

[Proposed Rules]

[Page 36215-36218]

From the Federal Register Online via GPO Access [wais.access.gpo.gov]

[DOCID:fr11jy01-28]

Proposed Rules Federal Register

This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules.

[[Page 36215]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-CE-04-AD]

RIN 2120-AA64

Airworthiness Directives; Raytheon Aircraft Company Beech Models 1900, 1900C (C-12J), and 1900D Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

SUMMARY: This document proposes to supersede Airworthiness Directive (AD) 95-02-18, which currently requires repetitive inspections of the engine truss assemblies for cracks on certain Raytheon Aircraft Company (Raytheon) Beech Models 1900, 1900C (C-12J), and 1900D airplanes, repair or replacement of any cracked engine truss assembly, and installation of reinforcement doublers. This proposed AD is the result of continued reports of fatigue cracks found on engine trusses on airplanes in compliance with AD 95-02-18. The proposed AD would require engine truss assembly replacement, periodic inspections and replacements, and the eventual incorporation of a cowling support installation kit as terminating action. The repetitive inspections of AD 95-02-18 would be retained until mandatory engine truss assembly replacement. The actions specified by the proposed AD are intended to detect and correct cracked engine truss assemblies, which could result in failure of the engine truss assembly and consequent loss of airplane control.

DATES: The Federal Aviation Administration (FAA) must receive any comments on this rule on or before August 30, 2001.

ADDRESSES: Submit comments in triplicate to FAA, Central Region, Office of the Regional Counsel, Attention: Rules Docket No. 2001-CE-04-AD, 901 Locust, Room 506, Kansas City, Missouri 64106. Comments may be inspected at this location between 8 a.m. and 4 p.m., Monday through Friday, holidays excepted.

Service information that applies to the proposed AD may be obtained from the Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201- 0085; telephone: (800) 625-7043 or (316) 676-4556. This information also may be examined at the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr. David L. Ostrodka, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4129; facsimile: (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Comments Invited

How Do I Comment on the 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 in triplicate to the address specified under the caption ADDRESSES. The FAA will consider all comments received on or before the closing date. We may amend the proposed rule in light of comments received. Factual information that supports your ideas and suggestions is extremely helpful in evaluating the effectiveness of the proposed AD action and determining whether we need to take additional rulemaking action.

Are There Any Specific Portions of the Proposed AD I Should Pay Attention To?

The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of the proposed rule that might suggest a need to modify the rule. You may examine 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 the proposed AD.

We are re-examining the writing style we currently use in regulatory documents, in response to the Presidential memorandum of June 1, 1998. That memorandum requires federal agencies to communicate more clearly with the public. We are interested in your comments on whether the style of this document is clear, and any other suggestions you might have to improve the clarity of FAA communications that affect you. You can get more information about the Presidential memorandum and the plain language initiative at http://www.plainlanguage.gov.

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-04-AD.'' We will date stamp and mail the postcard back to you.

Discussion

Has FAA Taken Any Action on the Engine Truss Assemblies of Raytheon Beech Models 1900, 1900C (C-12J), and 1900D Airplanes To This Point?

Continued problems with fatigue cracking of the engine truss assemblies on Raytheon Beech Models 1900, 1900C (C-12J), and 1900D airplanes caused FAA to issue AD 95-02-18, Amendment 39-9136 (60 FR 6652, February 3, 1995). This AD currently requires the following:

--Repetitive inspections of the engine truss assemblies for cracks; --Repair or replacement of any cracked engine truss assembly; and --Installation of reinforcement doublers.

What Has Happened Since AD 95-02-18 To Initiate This Action?

The FAA continues to receive reports of engine truss fatigue cracks on Raytheon Beech Models 1900, 1900C (C-12J), and 1900D airplanes. The reports reference airplanes that are in compliance with AD 95-02-18.

The fatigue cracks are developing as a result of operational stresses in joints, welded bracketry, and linoil holes sealed by drive screws.

Relevant Service Information

Has the Manufacturer Issued Service Information and What Are the Provisions of This Information?

Raytheon has issued the following service bulletins to address this subject:

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Service Bulletin

Provisions

Raytheon Aircraft Mandatory Includes instructions for inspecting the Service Bulletin SB 2255, part number (P/N) 114-910025-1, 118- Revision 10, Revised, June 910025-1, 118-910025-37, 118-910025-121, 1999.

and 129-910032-79 engine truss assemblies for fatigue cracks. Also includes procedures for replacing the engine truss assembly with a P/N 129- 910047 engine truss assembly. Raytheon Aircraft Mandatory Includes procedures for engine truss Service Bulletin SB 71-3144, assembly inspection and rework, Revision 1, Revised: April including: 1999.

--inspection of the linoil holes and replacement of the drive screws; --incorporation of a cowling support installation kit as terminating action for the inspections.

Raytheon Aircraft Mandatory Includes procedures for obtaining and Service Bulletin SB 71-3024, installing a placard that specifies the Issued: September 1997.

part number of the engine truss assembly.

The FAA's Determination and Explanation of the Provisions of the Proposed AD What Has FAA Decided?

After examining the circumstances and reviewing all available information related to the information described above, we have determined that:

--The unsafe condition referenced in this document exists or could develop on other Raytheon Beech Models 1900, 1900C (C-12J), and 1900D airplanes of the same type design; --The inspections specified in the above-referenced service information should be accomplished on the affected airplanes; and --AD action should be taken in order to detect and correct cracked engine truss assemblies, which could result in failure of the engine truss assembly and consequent loss of airplane control.

What Would the Proposed AD Require?

This proposed AD would supersede AD 95-02-18 with a new AD that would require engine truss assembly replacement, periodic inspections and replacements, and the eventual incorporation of a cowling support installation kit as terminating action. The repetitive inspections of AD 95-02-18 would be retained until mandatory engine truss assembly replacement.

Accomplishment of the proposed actions would be required in accordance with the previously-referenced service information.

Cost Impact

How Many Airplanes Would the Proposed AD Impact?

We estimate that the proposed AD affects up to 236 airplanes in the U.S. registry.

What Would Be the Cost Impact of the Proposed AD on Owners/Operators of the Affected Airplanes?

We estimate the following costs to accomplish the proposed actions:

Drive screw Engine truss inspection and Cowling support

Placard replacement

replacement kit installation installation

Number of Airplanes Affected.... 12................ 236............... 210............... 234 Cost Per Airplane: Workhours + 34 workhours x 4 workhours x 6 workhours x 1 workhour x $60 Parts Cost.

$60 per hour + $60 per hour + $60 per hour + per hour + $5 for $6,000 (average) $12 for parts = $35 for parts = parts = $65 per for parts =

$252 per airplane. $395 per airplane. airplane. $8,040 per airplane. Fleet Cost: Cost Per Airplane x $8,040 x 12 $252 x 236

$395 x 210

$65 x 234 Number of airplanes.

airplanes =

airplanes =

airplanes =

airplanes = $96,480.

$59,472.

$82,950.

$15,210.

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 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 14 CFR part 39 of the Federal Aviation Regulations 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 removing Airworthiness Directive (AD) AD 95-02-18, Amendment 39-9136 (60 FR 6652, February 3, 1995), and by adding a new AD to read as follows:

Raytheon Aircraft Company (Beech Aircraft Corporation formerly held Type Certificate (TC) No. A-24CE): Docket No. 2001-CE-04-AD; Supersedes AD 95-02-18, Amendment 39-9136.

(a) What airplanes are affected by this AD? This AD affects the following model and serial number airplanes that are certificated in any category:

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Model

Serial numbers

Beech Model 1900.......................... UA-2 and UA-3 Beech Model 1900C......................... UB-1 through UB-74 and UC-1 through UC-174 Beech Model 1900C (C-12J)................. UD-1 through UD-6 Beech Model 1900D......................... UE-1 through UE-302

(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 the AD are intended to detect and correct cracked engine truss assemblies, which could result in failure of the engine truss assembly and consequent loss of airplane control.

(d) What actions must I accomplish to address this problem on the affected airplanes? To address this problem, accomplish the following:

Action

Compliance

Procedures

(1) If you do not have a Inspect in

Inspect and replace part number (P/N) 129-

accordance with the in accordance with 910047-1, 129-910047-13, or schedule outlined the instructions in 129-910047-17 engine truss in the Appendix to Raytheon Aircraft assembly (or FAA-approved this AD (taken from Mandatory Service equivalent P/N) installed, AD 95-02-18, as Bulletin No. 2255. accomplish the following: specified in

Revision 10, (i) Inspect the engine truss Raytheon Aircraft Revised, June 1999. assembly for cracks and Mandatory Service Accomplishing the replace any cracked truss Bulletin No. 2255, inspection (only) with a P/N truss specified Revision 10,

using a previous in paragraph (d)(1)(ii) of Revised, June,

revision to this this AD; and.

1999). Replace

service bulletin is (ii) Replace the engine

within the next 100 acceptable. truss assembly with a P/N hours time-in- 129-910047-1, 129-910047- service (TIS) after 13, or 129-910047-17

the effective date assembly (or FAA-approved of this AD if the equivalent P/N)..

truss is not cracked and prior to further flight if the truss is cracked.

(2) For airplanes equipped Inspect upon

Accomplish with a P/N 129-910047-1 or accumulating 100 inspections and 129-910047-13 engine truss hours TIS on the replacements in assembly (or FAA-approved engine truss

accordance with equivalent P/N), inspect assembly or within Part I of the for linoil hole mislocation 25 hours TIS after ACCOMPLISHMENT and cracks in Area A as the effective date INSTRUCTIONS depicted in the referenced of this AD,

section of Raytheon service information and whichever occurs Aircraft Mandatory replace the engine truss later, unless

Service Bulletin SB assembly if any mislocated already

71-3144, Revision hole or crack is found

accomplished, and 1, Revised: April, during any inspection.

thereafter at

1999. intervals not to exceed 100 hours TIS. Accomplish any necessary engine truss assembly replacement prior to further flight where any mislocated hole or crack is found.

(3) For airplanes equipped Inspect upon

Accomplish with a P/N 129-910047-1 or accumulating 200 inspections, 129-910047-13 engine truss hours TIS on the repairs, and assembly (or FAA-approved engine truss

installations in equivalent P/N), accomplish assembly or within accordance with the following:

25 hours TIS after Part III of the (i) Inspect the engine

the effective date ACCOMPLISHMENT cowling support bracket for of this AD,

INSTRUCTIONS cracks and rework any

whichever occurs section of Raytheon cracked engine cowling

later, unless

Aircraft Mandatory support bracket; and.

already

Service Bulletin SB (ii) Install Kit No. 129- accomplished, and 71-3144, Revision 9017-1 reinforcements on thereafter at

1, Revised: April, the engine cowling support intervals not to 1999. bracket. The inspections exceed 200 hours required by paragraph

TIS. Accomplish any (d)(3)(i) of this AD are no necessary engine longer necessary when Kit cowling support No. 129-9017-1 is

rework prior to incorporated..

further flight where any cracked bracket is found. Install the engine cowling support bracket reinforcements upon accumulating 1,200 hours TIS on the engine truss assembly or within the next 100 hours TIS after the effective date of this AD, whichever occurs later.

(4) For airplanes equipped Upon accumulating Accomplish these with a P/N 129-910047-1 or 8,000 hours TIS on replacements in 129-910047-13 engine truss the engine truss accordance with assembly (or FAA-approved assembly or at the Part II of the equivalent P/N), replace next engine truss ACCOMPLISHMENT all remaining linoil drive assembly removal, INSTRUCTIONS screws (those not in Area whichever occurs section of Raytheon A). The inspections

later.

Aircraft Mandatory required by paragraph

Service Bulletin SB (d)(2) of this AD are no

71-3144, Revision longer required when these

1, Revised: April, screws are replaced.

1999.

(5) For airplanes equipped Within 12 months Accomplish this with a P/N 129-910047-1 or after the effective installation in 129-910047-13 engine truss date of this AD or accordance with the assembly (or FAA-approved upon installation ACCOMPLISHMENT equivalent P/N), install a of a P/N 129-910047- INSTRUCTIONS P/N 129-910047-15 truss 1 or 129-910047-13 section of Raytheon identification placard on engine truss

Aircraft Service the engine truss assembly. assembly, whichever Bulletin SB.71- occurs later.

3024, Issued: September, 1997.

(6) Do not install, on any As of the effective Not Applicable. affected airplane, an

date of this AD. engine truss assembly that is not P/N 129-910047-1, 129-910047-13, or 129- 910047-17 (or FAA-approved equivalent P/N).

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(e) Can I comply with this AD in any other way?

(1) You may use an alternative method of compliance or adjust the compliance time if:

(i) Your alternative method of compliance provides an equivalent level of safety; and

(ii) 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.

(2) Alternative methods of compliance approved in accordance with AD 95-02-18, which is superseded by this AD, are not approved as alternative methods of compliance with this AD.

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 Mr. David L. Ostrodka, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4129; 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 obtain copies of the documents referenced in this AD from the Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201- 0085. You may examine these documents at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106.

(i) Does this AD action affect any existing AD actions? This amendment supersedes AD 95-02-18, Amendment 39-9136.

Appendix to Docket No. 2001-CE-04-AD

The following is the compliance schedules for the inspections required in this AD. These are duplicated from AD 95-02-18, Amendment 39-9136:

1. For all affected airplanes having engine truss P/N 129- 910032-79 installed, initially and repetitively inspect the engine truss for cracks at the weld joints in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Beech SB 2255, Revision VI, dated August 1994, at the times specified in the following chart:

Area specified in Models

figure 1 of beech SB Initial inspection Repetitive inspections No. 2255, Rev. VI

1900 and 1900C....................... A...................... Upon accumulating 1,400 every 100 hours TIS *.

hours TIS 1900 and 1900C....................... B and C................ Upon accumulating 3,200 every 100 hours TIS *.

hours TIS 1900D................................ A...................... Upon accumulating 3,200 every 450 hours TIS *.

hours TIS 1900D................................ B and C................ Upon accumulating 3,200 every 3,000 hours TIS hours TIS *.

* or within the next 100 hours TIS after March 25, 1995 (the effective date of AD 95-02-18), whichever occurs later.

2. For all Models 1900 and 1900C airplanes having engine truss P/N 118-9100-25-37, P/N 118-910025-121, P/N 114-910025-1 or P/N 118- 910025-1, initially and repetitively inspect the engine truss for cracks at the weld joints in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Beech Service Bulletin (SB) 2255, Revision VI, dated August 1994, at the times specified in the following chart:

Area specified in figure 1

Repetitive of beech SB N. 2255, Rev. VI Initial inspection

inspections

A........................... Upon accumulating every 100 hours TIS 1,400 hours TIS *. B........................... Upon accumulating every 600 hours TIS 1,400 hours TIS *. C........................... Upon accumulating every 3,000 hours 1,400 hours TIS *. TIS

* or within the next 100 hours TIS after March 25, 1995 (the effective date of AD 95-02-18), whichever occurs later.

Issued in Kansas City, Missouri, on July 3, 2001. Dorenda D. Baker, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 01-17166Filed7-10-01; 8:45 am]

BILLING CODE 4910-13-P