[Federal Register Volume 59, Number 66 (Wednesday, April 6, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-8172]
[[Page Unknown]]
[Federal Register: April 6, 1994]
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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]
BILLING CODE 4910-13-U