Airworthiness Directives: Beech Aircraft Corporation 35 Series Airplanes

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93-CE-37-AD]

Airworthiness Directives: Beech Aircraft Corporation 35 Series

Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Supplemental notice of proposed rulemaking; Reopening of the

comment period.

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SUMMARY: This document proposes to provide additional time for the

public to comment on a proposal to supersede two airworthiness

directives that currently require the following on certain Beech

Aircraft Corporation (Beech) 35 series airplanes: Checking the

ruddervator static balance and adjusting as appropriate; fabricating

and installing airspeed limitation placards; incorporating certain

airspeed limitations into the airplane flight manual (AFM); and

installing stabilizer reinforcements. Several comments received on the

original notice of proposed rulemaking (NPRM) requested additional time

to respond to the proposed action. This proposed action would

incorporate and update the procedures and applicability of both AD's

into one document. The actions specified by the proposed AD are

intended to prevent structural failure of the V-tail, which could

result in loss of control of the airplane.

DATES: Comments must be received on or before June 17, 1994.

ADDRESSES: Submit comments in triplicate to the FAA, Central Region,

Office of the Assistant Chief Counsel, Attention: Rules Docket No. 93-

CE-37-AD, room 1558, 601 E. 12th Street, 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 Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas

67201-0085. This information also may be examined at the Rules Docket

at the address above.

FOR FURTHER INFORMATION CONTACT: Mr. Larry Engler, Aerospace Engineer,

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

Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4122;

facsimile (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to participate in the making of the

proposed rule by submitting such written data, views, or arguments as

they may desire. Communications should identify the Rules Docket number

and be submitted in triplicate to the address specified above. All

communications received on or before the closing date for comments,

specified above, will be considered before taking action on the

proposed rule. The proposals contained in this notice may be changed in

light of the comments received.

Comments are specifically invited on the overall regulatory,

economic, environmental, and energy aspects of the proposed rule. All

comments submitted will be available, both before and after the closing

date for comments, in the Rules Docket for examination by interested

persons. A report that summarizes each FAA- public contact concerned

with the substance of this proposal will be filed in the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments

submitted in response to this notice must submit a self-addressed,

stamped postcard on which the following statement is made: ``Comments

to Docket No. 93-CE-37-AD.'' The postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this NPRM by submitting a request

to the FAA, Central Region, Office of the Assistant Chief Counsel,

Attention: Rules Docket No. 93-CE-37-AD, room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106.

Discussion

A proposal to amend part 39 of the Federal Aviation Regulations to

include an AD that would apply to certain Beech 35 series airplanes was

published in the Federal Register on October 27, 1993 (58 FR 57760).

The action proposed to supersede AD 57-18-01 and AD 87-20-02 R1 with a

new AD that would require: (1) Checking the ruddervator static balance

and adjusting as appropriate; (2) fabricating and installing airspeed

limitation placards; (3) incorporating certain airspeed limitations

into the airplane flight manual (AFM); and (4) installing stabilizer

reinforcements. The proposed actions would be accomplished in

accordance with the instructions to either Beech Kit No. 35-4016-3, 35-

4016-5, 35-4016-7, or 35-4016-9, as applicable and as specified in

Beech Service Bulletin No. 2188, and the applicable maintenance

manuals.

Interested persons have been afforded an opportunity to participate

in the making of this amendment.

Several commenters request an extension of the comment period in

order to have additional time to respond to the actions presented in

the proposal. After careful consideration, the FAA has determined that

the comment period for the proposal should be reopened to allow the

public additional time to comment on the proposed actions.

The FAA has altered the proposal to include additional information

that was inadvertently left out or referenced incorrectly when

preparing the original notice of proposed rulemaking (NPRM). Before

final rule action is implemented, the FAA will evaluate all comments

received in response to the original NPRM as well as this supplemental

NPRM.

Since an unsafe condition has been identified that is likely to

exist or develop in other Beech 35 series airplanes of the same type

design, the proposed AD would supersede AD 57-18-01 and AD 87-20-02 R1

with a new AD that would require: (1) Checking the ruddervator static

balance and adjusting as appropriate; (2) fabricating and installing

airspeed limitation placards; (3) incorporating certain airspeed

limitations into the airplane flight manual (AFM); and (4) installing

stabilizer reinforcements. The proposed actions would be accomplished

in accordance with the instructions to either Beech Kit No. 35-4016-3,

35-4016-5, 35-4016-7, or 35-4016-9, as applicable and as specified in

Beech Service Bulletin No. 2188, and the applicable maintenance and

shop manuals.

The FAA estimates that approximately 10,200 airplanes in the U.S.

registry would be affected by the proposed AD, that it would take

approximately 40 workhours per airplane to accomplish the proposed

action, and that the average labor rate is approximately $55 an hour.

Parts cost approximately $500 per airplane. Based on these figures, the

total cost impact of the proposed AD on U.S. operators is estimated to

be $27,540,000. AD 57-18-01 and AD 87-20-02 R1, which both would be

superseded by the proposed action, currently require the same actions

as are proposed. This proposed action incorporates and updates the

procedures of both the current AD's into one document. With this in

mind, the proposed action would not provide any additional cost impact

upon U.S. operators than that which is already required.

The regulations proposed herein would 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

proposal would 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) 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, pursuant to 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. App. 1354(a), 1421 and 1423; 49 U.S.C.

106(g); and 14 CFR 11.89.

2. Section 39.13 is amended by removing both AD 57-18-01, Amendment

39-1759, and AD 87-20-02 R1, Amendment 39-5944, and by adding a new

airworthiness directive to read as follows:

Beech Aircraft Corporation: Docket No. 93-CE-37-AD. Supersedes AD

57-18-01, Amendment 39-1759, and AD 87-20-02 R1, Amendment 39-5944.

Applicability: 1. Models 35, 35R, A35, B35, C35, D35, E35, F35,

G35, H35, J35, K35, M35, N35, and P35 airplanes (all serial

numbers), certificated in any category;

2. Models S35, V35, V35A, and V35B airplanes (all serial

numbers), certificated in any category, that do not have the

straight tail conversion modification incorporated in accordance

with Supplemental Type Certificate (STC) SA2149CE; and

3. Model Super V airplanes (all serial numbers), certificated in

any category.

Compliance: Required initially within the next 100 hours time-

in-service (TIS) after the effective date of this AD, unless already

accomplished, and thereafter as indicated in the body of this AD.

To prevent structural failure of the V-tail, which could result

in loss of control of the airplane, accomplish the following:

Note 1: Any of the actions specified by this AD may have already

been accomplished in accordance with either AD 57-18-01 and AD 87-

20-02 R1, which are superseded by this AD. The intent of this AD is

to clarify, update, and incorporate the actions of those AD's into

one AD while maintaining the repetitive inspections schedules

already established by the superseded AD's.

Note 2: The paragraph structure of this AD is as follows:

Level 1: (a), (b), (c), etc.

Level 2: (1), (2), (3), etc.

Level 3: (i), (ii), (iii), etc.

Level 2 and Level 3 structures are designations of the Level 1

paragraph they immediately follow.

(a) For all airplane models, balance the elevator/rudder

(ruddervator) control surfaces in accordance with Section 3 of Beech

Shop Manual 35-590096B; and verify that the ruddervators are within

the manufacturers specified limits as specified in the applicable

shop or maintenance manual.

(1) If any ruddervator is found outside of the specified limits,

prior to further flight, obtain manufacturer's modification

instructions by contacting the Wichita Aircraft Certification Office

(ACO) at the address specified in paragraph (k) of this AD, and

modify the ruddervator in accordance with these instructions.

(2) Repeat these requirements any time the ruddervator is

repaired or painted.

(b) For all airplane models, visually inspect the fuselage

bulkheads at Fuselage Station (FS) 256.9 and FS 272 for damage

(cracks, distortion, loose rivets, etc.). Visually inspect the

fuselage skin around the bulkhead for damage (wrinkles or cracks).

Prior to further flight, repair or replace any damaged parts. Repeat

this inspection at each 100-hour TIS interval thereafter.

(c) For all Model Super V airplanes, check the static balance of

the ruddervator in accordance with Beech Shop Manual 35-590096A,

Section 3, pages 12A, 12B, and 13. Repeat this check anytime the

ruddervator is removed or repainted. Prior to further flight, make

applicable corrections if any of the following is not achieved:

(1) With the root weight removed and a tip weight attached,

static balance of 19.80 (plus or minus 1.00) inch-pounds tail heavy;

and

(2) With the root weight added to the condition specified in

paragraph (c)(1) of this AD, static balance of 7.00 (plus or minus

1.00) inch-pounds tail heavy.

(d) For Models 35, 35R, A35, B35, C35, D35, E35, F35, and G35

airplanes, accomplish the following:

(1) Fabricate a placard (utilizing letters of at least .10-inch

minimum height) with the words ``Never exceed speed, Vne, 144 MPH

(125 knots) IAS; Maximum structural cruising speed, Vno, 135 MPH

(117 knots) IAS; Maneuvering speed, VA, 127 MPH (110 knots) IAS.''

Install this placard on the airplane instrument panel next to the

airspeed indicator within the pilot's clear view.

(2) Mark the outside surface of the airspeed indicator with

lines of approximately \1/16\-inch by \3/16\-inch as follows:

(i) Red line at 144 MPH (125 knots);

(ii) Yellow line at 135 MPH (117 knots); and

(iii) A white slippage mark between the airspeed indicator glass

and case to visually verify glass has not rotated.

(3) Place a copy of this AD in the Pilot's Operating Handbook

(POH) and FAA-approved Airplane Flight Manual (AFM).

(e) For Models H35, J35, K35, M35, N35, P35, S35, V35, V35A, and

V35B, accomplish the following:

(1) Fabricate a placard (utilizing letters of at least .10-inch

minimum height) with the words ``Never exceed speed, Vne, 197 MPH

(171 knots) IAS; Maximum structural cruising speed, Vno, 177 MPH

(154 knots) IAS; Maneuvering speed, VA, 132 MPH (115 knots) IAS.''

Install this placard on the airplane instrument panel next to the

airspeed indicator within the pilot's clear view.

(2) Mark the outside surface of the airspeed indicator with

lines of approximately \1/16\-inch by \3/16\-inch as follows:

(i) Red line at 197 MPH (171 knots);

(ii) Yellow line at 177 MPH (154 knots); and

(iii) A white slippage mark between the airspeed indicator glass

and case to visually verify glass has not rotated.

(3) Place a copy of this AD in the Pilot's Operating Handbook

(POH) and FAA-approved Airplane Flight Manual (AFM).

(f) For all applicable model airplanes, fabricate a placard

(utilizing letters of at least .10-inch minimum height) with the

words ``Normal Category Operation Only'' and install this placard on

the instrument panel within the pilot's clear view over the existing

``Utility Category'' placard.

(g) For Models C35, D35, E35, F35, G35, H35, J35, K35, M35, N35,

S35, V35, V35A, and V35B airplanes, accomplish the following:

(1) Visually inspect the empennage, aft fuselage, and

ruddervator control system for damage in accordance with the

applicable Beech kits specified in Beech Service Bulletin (SB) No.

2188. Prior to further flight, accomplish the following in

accordance with these instructions:

(i) Replace or repair any damaged parts; and

(ii) Set the elevator controls, rudder and tab system controls,

cable tensions, and rigging.

(2) Remove all external stabilizer reinforcements installed

during incorporation of either Supplemental Type Certificate (STC)

SA845GL, STC SA846GL, STC SA1650CE, STC SA2286NM, or STC SA2287NM.

Seal or fill any residual holes with appropriate size rivets.

(i) The internal stub spar incorporated through SA1649CE and

SA1650CE may be retained.

(ii) The external angles incorporated through STC SA1649CE may

also be retained by properly trimming the leading edge section to

permit installing the stabilizer reinforcement referenced in

paragraph (g)(3) of this AD.

(3) Install stabilizer reinforcements in accordance with the

instructions to either Beech Kit No. 35-4016-3, 35-4016-5, 35-4016-

7, or 39-4016-9, as applicable and specified in Beech SB No. 2188.

Set the elevator nose down trim in accordance with the instructions

to either Beech Kit No. 35-4016-3, 35-4016-5, 35-4016-7, or 35-4016-

9, as applicable and specified in Beech SB No. 2188, and replace

ruddervator tab control cables with larger diameter cables in

accordance with the service information.

(h) Ensure correct accuracy of the airplane basic empty weight

and balance information by accomplishing one of the three methods

presented in Figures 1, 2a through 2c, and 3 of this AD. Prior to

further flight, correct any discrepancies in accordance with the

applicable maintenance manual.

Figure 1--Weight and Balance Information Accuracy Method No. 1

A. Review existing weight and balance documentation to assure

completeness and accuracy of the documentation from the most recent

FAA-approved weighing or from factory delivery to date of compliance

with this AD.

B. Compare the actual configuration of the airplane to the

configuration described in the weight and balance documentation; and

C. If equipment additions or deletions are not reflected in the

documentation or if modifications affecting the location of the

center of gravity (e.g., paint or structural repairs) are not

documented, determine the accuracy of the airplane weight and

balance data in accordance with Method No. 2.

Figure 2--Weight and Balance Information Accuracy Method No. 2

A. Assemble the following equipment:

1. One certified platform scale having a range of 750 to 1,000

pounds that is capable of supporting the nose wheel without

contacting the rest of the airplane;

2. One scale ramp of sufficient incline to allow rolling the

wheel onto the scale; and

3. One gear strut inflation system capable of inflating the gear

struts to full extension.

B. Procedure

1. Prepare the airplane for weighing in accordance with the

Weighing Instructions in the Weight and Balance Section of the

Pilot's Operating Handbook/Airplane Flight Manual (POH/AFM).

2. Ensure that the scale and airplane are on a level hangar

floor and the airplane is shielded from any wind.

3. Inflate the main landing gear struts to the maximum extension

and completely deflate the nose strut. Inflate the tires to correct

tire pressure as listed in the applicable maintenance or shop

manual.

Note: Extreme caution should be used when deflating the nose

strut because the airplane could drop suddenly.

4. Adjust the height of the scale platform to 12 inches above

the hangar floor.

5. Position the nose wheel onto the scale and ensure that the

remainder of the airplane does not contact the scale. Verify the

proper wheel weight. Set the parking brake and chock the main

wheels.

6. Record the net weight registered on the scale.

7. Remove the nose wheel from the scale.

8. Adjust the gear struts to the proper extension lengths in

accordance with the applicable maintenance or shop manual.

9. Subtract the following unusable (less undrainable) fuel from

the current airplane Basic Empty Weight, CG, and Moment:

------------------------------------------------------------------------

Weight

Category (lbs) Arm (in- Moment

(in.) lbs)

------------------------------------------------------------------------

All Airplanes................................ 34.5 79.1 2,730

Airplanes with 10-gallons wing auxiliary

tanks....................................... 5 94 470

Airplanes with 20-gallon auxiliary fuselage

tanks....................................... 3 133 399

------------------------------------------------------------------------

10. Multiply the net weight obtained in paragraph 6. by 83.25 to

obtain moment.

11. Divide the weight obtained in paragraph 9. into the moment

obtained in paragraph 10. to determine a value for X.

12. Calculate a value of CG from: CG=92.5-1.01X.

13. Subtract the CG obtained in paragraph 12. from the CG

obtained in paragraph 9.

D. Results

1. If the results of paragraph C. 13., indicate that the

difference in CG is equal to or less than .5 inches, then continue

to use the basic empty airplane weight and CG data listed in the

existing airplane records as the basis for computing the weight and

CG for the loaded airplane while using the criteria specified in the

POH/AFM, Weight and Balance Section.

2. If the results of paragraph C. 13, indicate that the

difference in CG is more than .5 inches, then determine the basic

weight and CG of the airplane using Method No. 3.

Example of Above--The following presents a sample calculation of

the information specified in Method 2:

Basic Empty Weight=2,064.5 lbs.

Arm=78.3 in.

Moment=161,650 in.-lbs.

Paragraph C. 6: Nose Wheel Weight--341 lbs

Paragraph C. 9:

------------------------------------------------------------------------

Weight

(lbs) Arm (in) Moment (in-lbs)

------------------------------------------------------------------------

2064.5 78.3 161,650

-34.5 79.1 -2,730

------------------------------------------------------------------------

2030.0 (*) 158,920

------------------------------------------------------------------------

*Arm=(18920)=78.29 (2030.)

Paragraph C.10.: Moment=(341 lbs) x (83.25 in)=28,388 in-lbs.

Paragraph C.11.: x =(23,388 in-lbs)=13.98 in. (2030.0 lbs)

Paragraph C.12.: CG=92.50 in.-(1.01) x (13.98)=78.38 in.

Paragraph C.13.: Difference=(78.29)-(78.38)=-.09 in.

Airplane is within plus/minus 0.5 tolerance, therefore paragraph

D.1., applies.

Figure 3--Weight and Balance Information Accuracy Method No. 3

Determine the basic empty weight and CG of the empty airplane

using the Weighing Instructions in the Weight and Balance Section of

the POH/AFM. Record the results in the airplane records, and use

these new values as the basis for computing the weight and CG

information as specified in the POH/AFM, Weight and Balances

Section.

(i) Upon completion of the requirements of paragraph (h) of this

AD, remove the placards required by paragraphs (d), (e), and (f) of

this AD (including all sub-paragraphs), as applicable, and observe

the original limits.

(j) Special flight permits may be issued in accordance with 14

CFR 21.197 and 21.199 to operate the airplane to a location where

the requirements of this AD can be accomplished.

(k) 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 ACO, FAA, 1801 Airport Road, Room

100, Wichita, Kansas 67209. The request should be forwarded through

an appropriate FAA Maintenance Inspector, who may add comments and

send it to the Manager, Wichita ACO.

Note: Information concerning the existence of approved

alternative methods of compliance with this AD, if any, may be

obtained from the Wichita ACO.

(l) Service information that applies to this AD may be obtained

from the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas

67201-0085. This information may also be inspected at the FAA,

Central Region, Office of the Assistant Chief Counsel, Room 1558,

601 E. 12th Street, Kansas City, Missouri.

(m) This amendment supersedes AD 57-18-01, Amendment 39-1759,

and AD 87-20-02 R1, Amendment 39-5944.

Issued in Kansas City, Missouri, on March 31, 1994.

John R. Colomy,

Acting Manager, Small Airplane Directorate, Aircraft Certification

Service.

[FR Doc. 94-8172 Filed 4-5-94; 8:45 am]

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