[Federal Register Volume 59, Number 211 (Wednesday, November 2, 1994)]
[Proposed Rules]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-27111]


[[Page Unknown]]

[Federal Register: November 2, 1994]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-CE-12-AD]

 

Airworthiness Directives; Beech Aircraft Corporation 33, 35, and 
36 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to supersede Airworthiness Directive 
92-08-07, which currently requires inspecting (one-time) the wing front 
spar carry-through frame structure for cracks on certain Beech 33, 35, 
and 36 series airplanes, and, if found cracked, repairing or 
reinforcing. The Federal Aviation Administration (FAA) has received 43 
reports of wing front spar carry-through frame structure cracks on the 
affected airplanes during the inspection required by AD 92-08-07. The 
proposed action would make this one-time inspection repetitive. The 
actions specified by the proposed AD are intended to prevent spar 
carry-through structure failure, which could result in severe 
structural damage to the wing.

DATES: Comments must be received on or before January 6, 1995.

ADDRESSES: Submit comments in triplicate to the FAA, Central Region, 
Office of the Assistant Chief Counsel, Attention: Rules Docket No. 94-
CE-12-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. 94-CE-12-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. 94-CE-12-AD, room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106.

Discussion

    AD 92-08-07, Amendment 39-8218 (57 FR 13004, April 15, 1992), 
currently requires inspecting (one-time) the wing front spar carry-
through frame structure for cracks on certain Beech 33, 35, and 36 
series airplanes, and, if found cracked, repairing or reinforcing. 
These actions are accomplished in accordance with Beech Service 
Bulletin (SB) No. 2360, dated November 1990.
    Since this AD became effective, the FAA has received 43 reports of 
wing front spar carry-through frame structure cracks on Beech 33, 35, 
and 36 series airplanes during the inspection required by AD 92-08-07. 
Several of these affected airplanes had cracks between huckbolts that 
incur heavy loads and along the radius of the carry-through web in 
critical primary airframe structure. These cracks, if not detected and 
corrected, could result in wing front spar carry-through structure 
failure, which could result in severe structural damage to the wing.
    After examining the circumstances and reviewing all available 
information related to the incidents described above, the FAA has 
determined that the inspection required by AD 92-08-07 should be 
repetitive.
    Since an unsafe condition has been identified that is likely to 
exist or develop in other Beech 33, 35, and 36 airplanes of the same 
type design, the proposed AD would supersede AD 92-08-07 with a new AD 
that would require repetitively inspecting the wing front spar carry-
through structure for cracks, and, if found cracked, repairing or 
replacing. The proposed action would be accomplished in accordance with 
Beech SB No. 2360, dated November 1990.
    The FAA estimates that 11,000 airplanes in the U.S. registry would 
be affected by the proposed AD, that it would take approximately 8 
workhours per airplane to accomplish the proposed action, and that the 
average labor rate is approximately $55 an hour. Based on these 
figures, the total cost impact of the proposed AD on U.S. operators is 
estimated to be $4,840,000. This figure does not account for repetitive 
inspections. The only difference between the cost analysis for this 
proposed action and AD 92-08-07 (which would be superseded by this 
proposed action) is the cost of these repetitive inspections. The FAA 
has no way of determining the number of repetitive inspections an 
owner/operator may incur.
    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 
part 39 of the Federal Aviation Regulations (14 CFR part 39) as 
follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing AD 92-08-07, Amendment 39-
8218 (57 FR 13004, April 15, 1992), and by adding a new airworthiness 
directive to read as follows:

Beech Aircraft Corporation: Docket No. 94-CE-12-AD; Supersedes AD 
92-08-07, Amendment 39-8218.

    Applicability: The following model and serial number airplanes, 
certificated in any category:

------------------------------------------------------------------------
                       Models                           Serial numbers  
------------------------------------------------------------------------
35-33, 35-A33, 35-B33, 35-C33, E33, F33, and G33....  CD-1 through      
                                                      CD-1304           
35-C33A, E33A, and F33A.............................  CE-1 through      
                                                      CE-1192           
E33C and F33C.......................................  CJ-1 through      
                                                      CJ-179            
H35, J35, K35, M35 N35, P35, S35, V35, V35A, and      D-4866 through    
 V35B.                                                D-10403           
36 and A36..........................................  E-1 through       
                                                      E-2397            
A36TC and B36TC.....................................  EA-1 through      
                                                      EA-471            
------------------------------------------------------------------------

    Compliance: Required initially upon the accumulation of 1,500 
hours time-in-service (TIS) or within the next 100 hours TIS after 
the effective date of this AD, whichever occurs later, unless 
already accomplished, and thereafter as indicated.
    To prevent spar carry-through structure failure, which could 
result in severe structural damage to the wing, accomplish the 
following:
    (a) Inspect the wing front spar carry-through frame (web) 
structure for cracks in accordance with the instructions in Beech 
Service Bulletin (SB) No. 2360, dated November 1990.
    (b) If cracks are found in the bend radius and not in the web 
face in the areas of the huckbolt fasteners during the inspection 
specified in paragraph (a) of this AD, accomplish the following at 
the time specified in accordance with the instructions in Beech SB 
No. 2360:
    (1) For cracks up to 2.25 inches, accomplish one of the 
following as applicable:
    (i) If not more than one crack on either side of the wing 
forward spar carry-through frame structure bend radius is found, 
prior to further flight, stop drill each crack at the crack ends. 
Within the next 200 hours TIS and thereafter at intervals not to 
exceed 200 hours TIS, reinspect each crack for progression and 
repair accordingly. Upon the installation of the applicable P/N 36-
4004 Kit, the repetitive inspection time may be extended to 500 
hours TIS.
    (ii) If more than one crack is found on either side of the wing 
forward spar carry-through frame structure bend radius, prior to 
further flight, install the applicable Beech P/N 36-4004 Kit, and 
reinspect thereafter at intervals not to exceed 500 hours TIS.
    (2) For cracks between 2.25 and 4.0 inches, accomplish one of 
the following as applicable:
    (i) If not more than one crack on either side of the wing 
forward spar carry-through frame structure bend radius is found, 
prior to further flight, stop drill each crack at the crack ends, 
and within the next 100 hours TIS, install the applicable Beech P/N 
36-4004 Kit. Reinspect thereafter at intervals not to exceed 500 
hours TIS.
    (ii) If more than one crack is found on either side of the wing 
forward spar carry-through frame structure bend radius, prior to 
further flight, install the applicable P/N 36-4004 Kit, and 
reinspect thereafter at intervals not to exceed 500 hours TIS.
    (3) For cracks exceeding 4.0 inches, prior to further flight, 
install the applicable Beech P/N 36-4004 Kit, and reinspect at 
intervals not to exceed 500 hours TIS.
    (c) If cracks are found in the web face in the area of the 
huckbolt fasteners but not in the bend radius during the inspections 
specified in paragraph (a) of this AD, accomplish the following at 
the time specified in accordance with the instructions in Beech SB 
No. 2360, but do not stop drill the cracks because it is possible to 
damage the structure behind the web face:
    (1) For cracks less than 1.0 inch in length, accomplish one of 
the following as applicable:
    (i) If not more than one crack on either side of the wing 
forward spar carry-through frame structure web face is found, within 
the next 200 hours TIS and thereafter at intervals not to exceed 200 
hours TIS, reinspect each crack for progression and repair 
accordingly. Upon the installation of the applicable P/N 36-4004 
Kit, the repetitive inspection time may be extended to 500 hours 
TIS.
    (ii) If more than one crack is found on either side of the wing 
forward spar carry-through frame structure web face, prior to 
further flight, install the applicable Beech P/N 36-4004 Kit, and 
reinspect thereafter at intervals not to exceed 500 hours TIS.
    (2) For cracks more than 1.0 inch in length, accomplish one of 
the following as applicable:
    (i) If not more than one crack on either side of the wing 
forward spar carry-through frame structure web area is found, within 
the next 25 hours TIS, install the applicable Beech P/N 36-4004 Kit. 
Reinspect thereafter at intervals not to exceed 500 hours TIS.
    (ii) If more than one crack is found on either side of the wing 
forward spar carry-through frame structure bend radius, prior to 
further flight, install the applicable Beech P/N 36-4004 Kit, and 
reinspect thereafter at intervals not to exceed 500 hours TIS.
    (3) If a crack passes through two fasteners but is less than 0.5 
inches beyond either fastener, accomplish one of the following as 
applicable:
    (i) If not more than one crack on either side of the wing 
forward spar carry-through frame structure web area is found, within 
the next 25 hours TIS, install the applicable Beech P/N 36-4004 Kit, 
and reinspect at intervals not to exceed 500 hours TIS.
    (ii) If more than one crack is found on either side of the wing 
forward spar carry-through frame structure bend radius, prior to 
further flight, install the applicable Beech P/N 36-4004 Kit, and 
reinspect at intervals not to exceed 500 hours TIS.
    (4) If a crack passes through two fasteners but is more than 0.5 
inches beyond either fastener, prior to further flight, install the 
applicable Beech P/N 36-4004 Kit. Reinspect thereafter at intervals 
not to exceed 500 hours TIS.
    (d) If cracks are found in both the web face in the area of the 
huckbolt fasteners and the bend radius during the inspections 
required in paragraph (a) of this AD, accomplish the following in 
accordance with the instructions in Beech SB No. 2360:
    (1) If only one crack is found on either side of the airplane, 
prior to further flight, repair each crack in accordance with the 
criteria and instructions in paragraphs (b)(1) through (b)(3) or 
(c)(1) through (c)(4) of this AD, as applicable. Reinspect 
thereafter at intervals not to exceed 500 hours TIS.
    (2) If more than one crack is found on either side of the 
airplane, accomplish one of the following as applicable:
    (i) For any crack that is 1.0 inch or more in length, prior to 
further flight, install the applicable Beech P/N 36-4004 Kit. 
Reinspect thereafter at intervals not to exceed 500 hours TIS.
    (ii) For any crack under 1.0 inch in length, within the next 200 
hours TIS and thereafter at intervals not to exceed 200 hours TIS, 
reinspect each crack for progression and repair accordingly. Upon 
the installation of the applicable P/N 36-4004 Kit, the repetitive 
inspection time may be extended to 500 hours TIS.
    (e) If a fuselage skin crack is found around the opening of the 
lower forward carry-through fitting, prior to further flight, obtain 
repair instructions from the manufacturer through the Wichita 
Aircraft Certification Office (ACO) at the address specified in 
paragraph (g) of this AD, and incorporate these instructions. 
Reinspect thereafter at intervals not to exceed 500 hours TIS.
    (f) Special flight permits may be issued in accordance with 
Secs. 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.
    (g) An alternative method of compliance or adjustment of the 
initial or repetitive compliance times that provides an equivalent 
level of safety may be approved by the Manager, Wichita 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: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Wichita ACO.
    (h) All persons affected by this directive may obtain copies of 
the document referred to herein upon request to the Beech Aircraft 
Corporation, P.O. Box 85, Wichita, Kansas 67201-0085; or may examine 
this document at the FAA, Central Region, Office of the Assistant 
Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 
64106.
    (i) This amendment supersedes AD 08-07, Amendment 39-8218.

    Issued in Kansas City, Missouri, on October 7, 1994.
Barry D. Clements,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 94-27111 Filed 11-1-94; 8:45 am]
BILLING CODE 4910-13-U