DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39 [62 FR 15533 No. 51, 3/17/97] [SN]	Raytheon Aircraft 
   Company (Beech)

Amendment 39-9968
Recurring: No

[Docket No. 96-CE-44-AD; Amendment 39-9968; AD 97-06-11]
RIN 2120-AA64
 
Airworthiness Directives; Raytheon Aircraft Company (Formerly Beech Aircraft Corporation) 35 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule

SUMMARY: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) 35 series airplanes (formerly referred to as Beech 35 series airplanes). This action requires inspecting the ruddervator differential tail control rod assembly for corrosion or cracks, repairing or replacing any cracked or corroded part, and applying anti-corrosion sealant to the ruddervator control pushrods. This action results from a report of a split in the ruddervator control push rod on an affected airplane that was found during a routine inspection. The split occurred when water froze in the internal area of the control push rod and then expanded. The actions specified by this AD are intended to prevent failure of the differential tail control rod assembly, which could result in loss of control of the airplane.

DATES: Effective May 16, 1997.
	The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of May 16, 1997.

ADDRESSES: Service information that applies to this AD may be obtained from the Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085. 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-44-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. Larry Engler, Aerospace Safety Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4122; facsimile (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of the This AD

	A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to certain Raytheon 35 series airplanes (formerly referred to as Beech 35 series airplanes) was published in the Federal Register as a notice of proposed rulemaking (NPRM) on October 18, 1996 (61 FR 54372). The NPRM proposed to require inspecting the ruddervator differential tail control rod assembly for corrosion or cracks, repairing or replacing any cracked or corroded part, and applying anti-corrosion sealant to the ruddervator control pushrods. Accomplishment of the proposed actions as specified in the NPRM would be in accordance with Raytheon Mandatory Service Bulletin (MSB) No. 2668, Issued: September, 1996.
	The NPRM was the result of a report of a split in the ruddervator control push rod on an affected airplane that was found during a routine inspection. The split occurred when water froze in the internal area of the control push rod and then expanded.
	Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposed AD or the FAA's determination of the cost to the public.
	Raytheon has revised MSB No. 2668 to clarify certain steps contained in the ACCOMPLISHMENT INSTRUCTIONS section. The FAA has determined that the AD could be accomplished in accordance with either Raytheon MSB No. 2668, Revised December, 1996; or Raytheon MSB No. 2668, Issued: September, 1996, and has incorporated this service bulletin revision into the final rule.

The FAA's Determination

	After careful review of all available information related to the subject presented above, the FAA has determined that air safety and the public interest require the adoption of the AD as proposed except for the incorporation of the revised service information and minor editorial corrections. The FAA has determined that this incorporation and the minor corrections will not change the meaning of the AD and will not add any additional burden upon the public than was already proposed.

Cost Impact

	The FAA estimates that 10,405 airplanes in the U.S. registry will be affected by this AD, that it will take approximately 4 workhours per airplane to accomplish the required action, and that the average labor rate is approximately $60 an hour. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $2,497,200. This figure is based on the presumption that no affected airplane will have a corroded or cracked part in the ruddervator differential tail control rod assembly that will need to be repaired or replaced. The FAA has no way of determining how many ruddervator control push rods that will be corroded or cracked.

Regulatory Impact

	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.
	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) 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 final evaluation prepared for this action is contained 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, 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.

Sec. 39.13   [Amended]

	2. Section 39.13 is amended by adding a new airworthiness directive (AD) to read as follows:

97-06-11  RAYTHEON AIRCRAFT COMPANY (formerly Beech Aircraft Corporation): Amendment 39-9968; Docket No. 96-CE-44-AD.

	Applicability: Models 35, 35R, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35TC, V35A, V35A-TC, V35B, and V35B-TC airplanes, serial numbers D-1 through D-10403, D-15001, and D-15002, certificated in any category.

	Note 1: This AD applies to each airplane 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 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 (d) 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 within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished.

	To prevent failure of the ruddervator differential tail control rod assembly, which could result in loss of control of the airplane, accomplish the following:
   (a)	Inspect the ruddervator differential tail control rod assembly for cracks and corrosion in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Raytheon Mandatory Service Bulletin (MSB) No. 2668, Revised: December, 1996; or Raytheon MSB No. 2668, Issued: September, 1996. Prior to further flight, repair or replace any corroded or cracked part as specified in and in accordance with the service information referenced above.
   (b)	Apply anti-corrosion sealant to the ruddervator control pushrods in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Raytheon MSB No. 2668, Revised: December, 1996; or Raytheon MSB No. 2668, Issued: September, 1996.
   (c)	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 airplane to a location where the requirements of this AD can be accomplished.
   (d)	An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO.

	Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO.

   (e)	The inspection, repair or replacement (if necessary), and application required by this AD shall be done in accordance with either Raytheon Mandatory Service Bulletin No. 2668, Issued: September, 1996; or Raytheon Mandatory Service Bulletin No. 2668, Revised: December, 1996. 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 the Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
   (f)	This amendment (39-9968) becomes effective on May 16, 1997.

	Issued in Kansas City, Missouri, on March 7, 1997.

Michael Gallagher, Manager, Small Airplane Directorate, Aircraft Certification Service.

FOR FURTHER INFORMATION CONTACT: Mr. Larry Engler, Aerospace Safety Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4122; facsimile (316) 946-4407.

Manufacturer's Service Information: Included Below.
Raytheon Mandatory Service Bulletin No. 2668 and No. 2668 Revised

Copies may be obtained from the Raytheon Aircraft Company, P.O. Box 85, Wichita, 
Kansas 67201-0085.

RAYTHEON AIRCRAFT
SERVICE BULLETIN NO. 2668, Rev. I
MANDATORY SERVICE BULLETIN
Model Beech 35 Series
ATA Code 27-20
Issued: 	September 1996
Revised: 	December 1996

SUBJECT:
FLIGHT CONTROLS - RUDDERVATOR DIFFERENTIAL TAIL CONTROL ROD ASSEMBLY INSPECTION/MODIFICATION

SYNOPSIS OF CHANGE:
If the Original Issue of this Service Bulletin has been complied with, no further action is required.
This Revision modifies the MATERIAL list to include easily obtainable products for the consumable materials contained in the list. The revision also clarifies some of the steps listed under the 

ACCOMPLISHMENT INSTRUCTIONS.

REASON:
This Service Bulletin is being issued to inspect the two existing P/N 35-524106 or P/N 35-524106-8 ruddervator differential tail control rod assemblies for moisture and corrosion, repair or replace the assemblies (if necessary), seal the assemblies against moisture intrusion, and reidentify the modified assemblies.
Each differential tail control rod assembly has two rod ends which are installed in the ends of the assembly. These rod ends have a hollow shaft which is open at both ends and extends through the length of the rod end. It appears that through the process of the rod assembly "breathing", moisture laden air enters the rod assembly through the hollow shaft in the rod ends and condenses in the rod assembly tube. The accumulation of moisture in the assembly tube, in the presence of freezing temperatures, may cause the tube to split and possibly lead to the ruddervator not operating properly.
   NOTE
In 1981, Service Instructions (SI) No. 0989 was issued to address internal corrosion of the ruddervator differential tail control rod assemblies. SI No. 0989 directed that an inspection and anticorrosion treatment be performed on the rod assemblies, but did not seal the rod ends to prevent the intrusion of moisture into the rod assembly tubes. Irrespective of prior compliance with SI No. 0989, this Mandatory Service Bulletin (No. 2668) must be accomplished.

EFFECTIVITY:
BEECH Bonanza Models 35, 35R, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35TC, V35A, V35A-TC, V35B, and V35B-TC, serials D-1 through D-10403, D-15001, and D-15002.

COMPLIANCE:
Raytheon Aircraft Company considers this to be a mandatory modification and it must be accomplished as soon as possible after receipt of this Service Bulletin, but no later than the next scheduled inspection after receipt of this Service Bulletin.
An Airworthiness Directive has been requested on the matter covered by this Service Bulletin.

APPROVAL:
Engineering data contained in this Service Bulletin is FAA Approved.

MANPOWER:
The following information is for planning purposes only:
Estimated man-hours to inspect and replace: 2 hours.
Estimated man-hours to inspect/seal/reidentify: 2 hours.
Suggested number of men: 1 man.
The above is an estimate based on experienced, properly equipped personnel complying with this Service Bulletin. Occasionally, after work has started, conditions may be found which could result in additional man-hours.

MATERIAL:
The following parts and materials required for this modification may be ordered through a Raytheon Aircraft Authorized Service Center. Some of the materials may be obtained locally.

                                                                    Quantity Per
Part Number              Description                                  Airplane
35-524106-11 (*)     Differential Tail Control                      As Required
or                   Rod Assembly
35-524106-13 (**)

35-524106-2 (*)      Tube                                           As Required
or
35-524106-6 (**)

131765-8M (***)      Rod End                                        As Required
or
35-524106-9 (***)

AN316-6R             Nut                                            As Required

MIL-S-8802,          Sealant (i.e. PR-1440, Pro Seal 890 B-1/2,     As Required
Class B              MC 236)

MIL-C-38736 or       Solvent                                        As Required
equivalent (****)

MIL-C-16173,         Corrosion Preventative Compound (i.e.          As Required
Grade 2              Braycote 137)

MIL-C-22750 (FED-    Orange Epoxy, Enamel, or Polyurethane          As Required
STD-595, Color No.   Paint
12246) or equiva-
lent

MIL-G-23827          Grease (i.e. Aeroshell 7)                      As Required

MIL-P-23377          Epoxy Polyamide Primer                         As Required

TT-N-95, Type II     Naphtha (Aliphatic)                            As Required

P-D-680, Type I      Mineral Spirits                                As Required

MIL-C-5541           Alodine 1200                                   As Required

(*) Serials D-1 through D-5725.
(**) Serials D-5726 through D-10403, D-15001, and D-15002.
(***) It is permissible to mix or match P/N 131765-8M and P/N 35-524106-9 rod ends on the same differential tail control rod assembly.
(****) MEK or MPK may be used as an alternate.
Raytheon Aircraft Company expressly reserves the right to supersede, cancel, and/or declare obsolete, without prior notice, any parts or publications that may be referenced in this Service Bulletin.

SPARES AFFECTED:
Remove all P/N 131765-3M and P/N MD46-15 rod ends from stock. Modify and reidentify the rod ends in accordance with step 12 of the ACCOMPLISHMENT INSTRUCTIONS. Refer to Figure 1 as required. Return the reidentified rod ends to stock.
Remove all P/N 35-524306 and P/N 35-524306-8 differential tail control rod assemblies from stock. Modify and reidentify the rod assemblies in accordance with steps 4 through 7 and steps 11 through 18 of the ACCOMPLISHMENT INSTRUCTIONS. Refer to Figure 1 as required. Return the reidentified rod assemblies to stock.

WARRANTY CREDIT:
None.

SPECIAL TOOLS:
None.

WEIGHT AND BALANCE:
Negligible.

REFERENCES:
FAA Aircraft Inspection and Repair Manual, P/N AC43.13-1A, Paragraph 300;
BEECHCRAFT Model 35 Shop Manual, P/N 35-590096B18 or subsequent, Section 3;
BEECHCRAFT Bonanza 33, 35, 36 Series Maintenance Manual, P/N 36-590001-9 revision A17 or subsequent, Chapter 27-21;
BEECHCRAFT Bonanza Illustrated Parts Catalog for Models H35 through V35A-TC, P/N 35-590015 revision C5 or subsequent;
BEECHCRAFT Bonanza Illustrated Parts Catalog for Models 35 through G35, P/N 35-590028 revision B4 or subsequent;
BEECHCRAFT Bonanza Illustrated Parts Catalog for Models V35B, P/N 35-590102 revision E4 or subsequent.

PUBLICATIONS AFFECTED:
It is recommended that a note "See Service Bulletin No. 2668, Rev. I" be made in the following:
BEECHCRAFT Model 35 Shop Manual, PIN 35-590096B18 or subsequent, Section 3;
BEECHCRAFT Bonanza 33, 35, 36 Series Maintenance Manual, P/N 36-590001-9 revision A17 or subsequent, Chapter 27-21;
BEECHCRAFT Bonanza Illustrated Parts Catalog for Models H35 through V35A-TC, P/N 35-590015 revision C5 or subsequent;
BEECHCRAFT Bonanza Illustrated Parts Catalog for Models 35 through G35, P/N 35-590028 revision B4 or subsequent;
BEECHCRAFT Bonanza Illustrated Parts Catalog for Models V35B, P/N 35-590102 revision E4 or subsequent.

ACCOMPLISHMENT INSTRUCTIONS:
This Service Bulletin shall be accomplished as follows:

   NOTE
Should any difficulty be encountered in accomplishing this Service Bulletin, contact Raytheon Aircraft Company at 1-800-625-7043.

   1.	Remove all power from the aircraft and disconnect the battery.
   2.	Remove the tail cone and any access covers/panels required to gain access to the two ruddervator differential tail control rod assemblies.
   3.	Identify by left and right location and remove the existing P/N 35-524106 or P/N 35-524106-8 differential tail control rod assemblies. Refer to Figure 1.
   4.	Accurately measure and record the length of each rod assembly. The measurement is taken from the center of one rod end bolt hole to the center of the other rod end bolt hole.
   5.	Loosen the nuts and remove the rod ends from each rod assembly.
   6.	Remove the nuts from the rod ends.
   7.	Thoroughly clean the rod ends, nuts, and the interior and exterior of the rod assembly tubes with P/N MIL-S-38736 solvent and allow to dry.
   8.	Inspect the rod ends, nut, and tubes for cracks and corrosion in accordance with the dye penetrant procedures listed in the P/N AC43.13-1A FAA Aircraft Inspection and Repair Manual, paragraph 300.
   9.	Smooth any minor nicks, dents, and scratches that are less than 0.010 inch deep. Apply P/N MIL-C-5541 Alodine 1200 to any areas of bare metal and prime with P/N MIL-P-23377D, Type I epoxy polyamide primer.
   10.	If cracks or corrosion are found or the threads are damaged, reference the MATERIAL section and replace the affected part.

   NOTE
- If a complete rod assembly is required, obtain the new assembly (listed in the MATERIAL section) and adjust the rod ends to obtain the length of the original rod assembly (step 4). Tighten the nuts to secure the rod ends and proceed to step 19 to complete the instructions for the new rod assembly.
- It is permissible to mix or match P/N 131765-8M and P/N 35-524106-9 rod ends on the same differential tail control rod assembly.

   11.	If no cracks or corrosion are found in the tubes, perform the following:
	a.	Blow clean, dry, filtered shop air through each tube to remove all moisture.
	b.	Fill the interior of each tube with P/N MIL-C-16173, Grade 2 corrosion preventative compound diluted with enough P/N TT-N-95, Type II aliphatic naphtha or P/N P-D-680 mineral spirits to sufficiently allow flowability. Drain off the excess solution and allow to dry.
   12.	If no cracks or corrosion are found in the rod ends, perform the following:
	a.	Clean the hollow shaft in each rod end with solvent and allow to dry.
	b.	Fill the hollow shaft with P/N MIL-S-8802, Class B sealant and allow to cure.
	c.	After the sealant has cured, lubricate the ball and groove in the rod end insert with P/N MIL-G-23827 grease.
	d.	Reidentify the modified rod end as P/N 35-524106-9 using an indelible marker.
   13.	Apply P/N MIL-C-22750 orange epoxy, enamel, or polyurethane paint to the first two inches of each tube end and allow to dry. If corrosion preventative compound is present where the paint is to be applied, remove it with P/N MIL-C-38736 solvent before painting.

   NOTE
The application of orange paint to the rod assembly tube provides a readily identifiable indication that the tube has been treated with corrosion preventative compound and that the rod ends have been sealed.

   14.	Install the nuts on the rod ends.
   15.	Lubricate the rod end threads with corrosion preventative compound and install the rod ends in the rod assembly tube.

   CAUTION
In order to insure adequate thread engagement, be sure that the rod end threads are visible in the rod assembly tube inspection holes (located at both ends of the tube) after the rod ends have been adjusted to obtain the recorded length. If the inspection holes are not present, be sure that the engaged rod end does not extend more than 1 5/8 inches past the end of the tube (distance is measured from the end of the tube to the center of the rod end insert).
   16.	Adjust the rod ends until the rod assembly is the same length recorded in step 4.
   17.	Tighten the nuts to secure the rod ends.
   18.	Reidentify the modified rod assemblies using an indelible marker as follows:
	a.	The modified P/N 35-524106 rod assemblies become P/N 35-524106-11 rod assemblies.
	b.	The modified P/N 35-524106-8 rod assemblies become P/N 35-524106-13 rod assemblies.
   19.	Install the rod assemblies per the left and right identification established in step 3.
   20.	Operate the ruddervator controls to insure proper operation of the differential tail control rod assemblies and the ruddervator.
   21.	Install the tail cone and any access panels/covers that were removed to facilitate this Service Bulletin.
   22.	Restore power to the aircraft and connect the battery.
   23.	Return the aircraft to service.

RECORD COMPLIANCE:
Upon completion of this Service Bulletin, make an appropriate maintenance record entry.

   NOTE
If you are no longer in possession of this airplane, please forward this information to the present owner.

FIGURE 1

Raytheon Aircraft Company (RAC) issues Service information for the benefit of owners and fixed based operators in the form of two classes of Service Bulletins. The first class, Mandatory Service Bulletins (red border) includes changes, inspections and modifications that could affect safety or crashworthiness. RAC considers compliance with these Service Bulletins to be mandatory. RAC also issues Service Bulletins with no border which are designated as either recommended or optional in the compliance section within the bulletin. In the case of recommended Service Bulletins, RAC feels the changes, modifications, improvements or inspections will benefit the owner/operator and although highly recommended, Recommended Service Bulletins are not considered mandatory at the time of issuance. In the case of optional Service Bulletins, compliance with the changes, modifications, improvements or inspections is at the owner/operator's discretion. Both classes are mailed to:
   (a)	RAC Authorized Service Center.
   (b)	Owners of record on the FAA Aircraft Registration Branch List and the RAC International Owner Notification Service List.
   (c)	Those having a publications subscription.
Information on Owner Notification Service or subscriptions can be obtained though any RAC Authorized Service Center. As Mandatory Service Bulletins and Service Bulletins are issued, temporary notification in the Service Bulletin Master Index should be made until the index is revised. Warranty will be allowed only when specifically defined in the Service Bulletin and in accordance with the RAC Warranty Policy.
Unless otherwise designated, RAC Mandatory Service Bulletins, Service Bulletins and RAC Kits are approved for installation on RAC airplanes in original or RAC modified configurations only. RAC Mandatory Service Bulletins, Service Bulletins and Kits may not be compatible with airplanes modified by STC installations or modifications other than RAC approved kits.

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