[Federal Register Volume 60, Number 192 (Wednesday, October 4, 1995)]
[Proposed Rules]
[Pages 51942-51944]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-24605]



=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-CE-46-AD]


Airworthiness Directives; Beech Aircraft Corporation Models 1900, 
1900C, and 1900D Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes to adopt a new airworthiness directive 
(AD) that would apply to certain Beech Aircraft Corporation (Beech) 
Models 1900, 1900C, and 1900D airplanes that do not have canted 
bulkhead Repair Kit No. 129-4005-1 S incorporated. The proposed action 
would require repetitively inspecting the canted bulkhead located at 
Fuselage Station 588.10 for cracks, and, if cracks are found that 
exceed certain limits, incorporating canted bulkhead Repair Kit No. 
129-4005-1 S as terminating action for the repetitive inspection 
requirement. Numerous reports of multi-site cracks occurring in the 
canted bulkhead at Fuselage Station 588.10 on the affected airplanes 
prompted the proposed action. The actions specified by the proposed AD 
are intended to prevent the inability of the bulkhead to carry its 
ultimate design load because of cracks in the canted bulkhead, which, 
if not detected and corrected, could affect rudder cable tension and 
result in reduced rudder power.

DATES: Comments must be received on or before December 4, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket No. 95-CE-46-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. Steve Potter, Aerospace Engineer, 
Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-
Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4124; 
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 

[[Page 51943]]
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. 95-CE-46-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. 95-CE-46-AD, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106.

Discussion

    The FAA has received numerous reports of multi-site cracks in the 
canted bulkhead at Fuselage Station 588.10 on three Beech Models 1900, 
1900C, and 1900D airplanes. Specifically, these cracks were found at 
the outer flange radius and outer flange stringer cutouts of the canted 
bulkhead. This condition, if not detected and corrected, could prevent 
the bulkhead from carrying its ultimate design load because of cracks 
in the canted bulkhead, which, if not detected and corrected, could 
affect rudder cable tension and result in reduced rudder power.
    Beech has issued Service Bulletin (SB) No. 2564, Revision 1, dated 
April 1995, which specifies procedures for inspecting the canted 
bulkhead at Fuselage Station 588.10. This service bulletin also 
references canted bulkhead Repair Kit No. 129-4005-1 S, which, when 
incorporated on the affected airplanes, reinforces this area at 
Fuselage Station 588.10.
    After examining the circumstances and reviewing all available 
information related to the incidents described above including the 
referenced service information, the FAA has determined that AD action 
should be taken to prevent the inability of the bulkhead to carry its 
ultimate design load because of cracks in the canted bulkhead, which, 
if not detected and corrected, could affect rudder cable tension and 
result in reduced rudder power.
    Since an unsafe condition has been identified that is likely to 
exist or develop in other Beech Models 1900, 1900C, and 1900D airplanes 
of the same type design that do not have canted bulkhead Repair Kit No. 
129-4005-1 S incorporated, the proposed AD would require repetitively 
inspecting the canted bulkhead located at Fuselage Station 588.10 for 
cracks, and, if cracks are found that exceed certain limits, 
incorporating canted bulkhead Repair Kit No. 129-4005-1 S as 
terminating action for the repetitive inspection requirement. 
Accomplishment of the proposed inspections would be in accordance with 
Beech SB No. 2564, Revision 1, dated April 1995. Accomplishment of the 
proposed possible reinforcement would be in accordance with the 
instructions included with the above referenced kit.
    The FAA estimates that 364 airplanes in the U.S. registry would be 
affected by the proposed AD, that it would take approximately 2 
workhours per airplane to accomplish the proposed inspections, and that 
the average labor rate is approximately $60 an hour. Based on these 
figures, the total cost impact of the proposed AD on U.S. operators is 
estimated to be $43,680. This figure does not take into account the 
number of repetitive inspections an affected airplane owner/operator 
would incur and is based on the assumption that no canted bulkhead 
would be found cracked during the inspection. The FAA has no way of 
determining the number of repetitive inspections a particular airplane 
owner/operator would incur or how many canted bulkheads would be found 
cracked during the proposed inspections. This figure also does not take 
into account the number of affected airplane owners/operators that may 
have incorporated the inspection-terminating reinforcement kit.
    Beech has notified the FAA that 36 reinforcement kits have been 
distributed to the affected airplane owners/operators. If each of the 
kits has been installed on an affected airplane, then the inspection 
requirement for these airplanes is eliminated. Based on this 
assumption, the cost impact of the proposed AD upon U.S. owners/
operators of the affected airplanes would be reduced $4,320 from 
$43,680 to $39,360.
    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 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

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

Beech Aircraft Corporation: Docket No. 95-CE-46-AD.
    Applicability: The following airplane models and serial numbers, 
certificated in any category, that do not have canted bulkhead 
Repair Kit No. 129-4005-1 S incorporated:

------------------------------------------------------------------------
               Model                             Serial Nos.            
------------------------------------------------------------------------
1900...............................  UA-1 through UA-3.                 
1900C..............................  UB-1 through UB-74 and UC-1 through
                                      UC-174.                           
1900C (C12J).......................  UD-1 through UD-6.                 
1900D..............................  UE-1 through UE-113.               
------------------------------------------------------------------------

    Note 1: This AD applies to each airplane identified in the 
preceding applicability revision, 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 the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it. Compliance: Required as indicated in the 

[[Page 51944]]
body of this AD, unless already accomplished.
    To prevent the inability of the bulkhead to carry its ultimate 
design load because of cracks in the canted bulkhead, which, if not 
detected and corrected, could affect rudder cable tension and result 
in reduced rudder power, accomplish the following:

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

Level 1: (a), (b), (c), etc.
Level 2: (1), (2), (3), etc.

    Level 2 structures are designations of the Level 1 paragraph 
they immediately follow.
    (a) Upon the accumulation of 5,000 hours time-in-service (TIS) 
or within the next 600 hours TIS, whichever occurs later, inspect 
the canted bulkhead at Fuselage Station 588.10. Accomplish this 
inspection in accordance with the Accomplishment Instructions 
section of Beech Service Bulletin (SB) No. 2564, Revision 1, dated 
April 1995.
    (b) If, during the inspection, one or more of the limits 
specified in paragraphs (b)(1), (b)(2), or (b)(3) of this AD are 
found (also specified in Beech SB No. 2564), prior to further 
flight, incorporate Beech Kit No. 129-4005-1 S, which reinforces the 
canted bulkhead at Fuselage Station 588.10.
    (1) Any one crack that is greater than 2.5 inches in length.
    (2) The sum of all crack lengths in any 12 inches of consecutive 
frame length is greater than 4.0 inches
    (3) Any crack that progresses through the width of the bulkhead.
    (c) If no cracks are found during an inspection or a crack is 
found that does not exceed one of the limits specified in paragraphs 
(b)(1), (b)(2), or (b)(3) of this AD, accomplish one of the 
following:
    (1) Repeat the inspection specified in paragraph (a) of this AD 
at intervals not to exceed 600 hours TIS, and prior to further 
flight, reinforce the canted bulkhead as specified in paragraph (b) 
of this AD if cracks are found that exceed one or more of the limits 
specified in paragraphs (b)(1), (b)(2), or (b)(3) of this AD; or
    (2) Within 600 hours after the last canted bulkhead inspection, 
incorporate Beech Kit No. 129-4005-1 S. Incorporating this kit 
reinforces the canted bulkhead at Fuselage Station 588.10.
    (d) 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.
    (e) 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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Wichita ACO.

    (f) 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.

    Issued in Kansas City, Missouri, on September 26, 1995.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-24605 Filed 10-3-95; 8:45 am]
BILLING CODE 4910-13-U