[Federal Register Volume 61, Number 115 (Thursday, June 13, 1996)]
[Proposed Rules]
[Pages 29994-29996]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-14989]



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


DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 96-CE-11-AD]
RIN 2120-AA64


Airworthiness Directives; Beech Aircraft Corporation 90, 99, 100, 
200, and 1900 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes to supersede AD 92-27-10, which 
currently requires inspecting the pilot and copilot chairs to ensure 
that the locking pins will fully engage in the seat tracks on certain 
Beech Aircraft Corporation (Beech) 90, 99, 100, 200, and 1900 series 
airplanes, and modifying any chair where any locking pin fails to fully 
engage or is misaligned. Reports of pilot and copilot chair locking pin 
malfunctions prompted AD 92-27-10. Since issuance of that AD, the 
Federal Aviation Administration (FAA) has determined that additional 
airplanes should be affected by the pilot and copilot chair locking 
pins inspection and modification (if required), and that the inspection 
should be accomplished in accordance with revised procedures. The 
proposed action would retain the inspection and modification 
requirements of AD 92-27-10; incorporate additional airplanes into the 
applicability over that included in AD 92-27-10; and require the 
inspection in accordance with revised service information. The actions 
specified by the proposed AD are intended to prevent inadvertent 
movement of the pilot or copilot chair, which could result in loss of 
control of the airplane if it occurs during a critical flight maneuver.

DATES: Comments must be received on or before August 16, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket No. 96-CE-11-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 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. 96-CE-11-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. 96-CE-11-AD, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106.

Discussion

    AD 92-27-10, Amendment 39-8444 (58 FR 5923, January 25, 1993), 
currently requires the following on certain Beech Aircraft Corporation 
(Beech) 90, 99, 100, 200, and 1900 series

[[Page 29995]]

airplanes: inspecting the pilot and copilot chairs to ensure that the 
locking pins will fully engage in the seat tracks, and modifying any 
chair where any locking pin fails to fully engage or is misaligned. 
Accomplishment of the inspection required by AD 92-27-10 is in 
accordance with Beech Service Bulletin (SB) No. 2444, Revision 1, dated 
September 1992.
    Reports of pilot and copilot chair locking pin malfunctions, 
including one instance where the pilot chair slid back from the full 
forward position, prompted the FAA to issue AD 92-27-10. Since issuance 
of that AD, the FAA has determined that additional airplanes should be 
affected by the pilot and copilot chair locking pins inspection and 
modification, and that the inspection should be accomplished in 
accordance with revised procedures.

Applicable Service Information

    The Beech Aircraft Corporation has revised SB No. 2444 to the 
Revision II level (dated May 1995). The SB revision updates airplane 
serial number effectivity, and incorporates an additional procedure to 
Step 5 of the ACCOMPLISHMENT INSTRUCTIONS section.

Evaluation of All Applicable Information

    After examining the circumstances and reviewing all available 
information related to the incidents described above, including the 
referenced SB revision, the FAA has determined that AD action should be 
taken to prevent inadvertent movement of the pilot or copilot chair, 
which could result in loss of control of the airplane if it happens 
during a critical flight maneuver.

Explanation of the Provisions of the Proposed AD

    Since an unsafe condition has been identified that is likely to 
exist or develop in other Beech 90, 99, 100, 200, and 1900 series 
airplanes of the same type design, the proposed AD would supersede AD 
92-27-10 with a new AD that would (1) retain the requirement of 
inspecting the pilot and copilot chairs to ensure that the locking pins 
will fully engage in the seat tracks, and modifying any chair where any 
locking pin fails to fully engage or is misaligned; (2) incorporate 
additional airplanes into the applicability over that included in AD 
92-27-10; and (3) require the inspection in accordance with Beech SB 
No. 2444, Revision II, dated May 1995.

Cost Impact

    The FAA estimates that 4,971 airplanes in the U.S. registry would 
be affected by the proposed AD, that it would take approximately 1 
workhour per airplane to accomplish the proposed inspection, and that 
the average labor rate is approximately $60 an hour. No parts are 
required to accomplish the proposed action. Based on these figures, the 
total cost impact of the proposed AD on U.S. operators is estimated to 
be $298,260. This figure only takes into account the cost of the 
inspection and does not take into account the cost of modifying any 
pilot or copilot seat where the locking mechanism fails to fully engage 
or is misaligned. If a pilot or copilot seat fails to fully engage or 
is misaligned, the modification would take approximately 2 workhours 
per airplane at an average labor rate of $60 per hour ($120 per 
airplane).

Regulatory Impact

    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 USC 106(g), 40113, 44701.


Sec. 39.13   [Amended]

    2. Section 39.13 is amended by removing Airworthiness Directive 
(AD) 92-27-10, Amendment 39-8444 (58 FR 5923, January 25, 1993), and by 
adding a new AD to read as follows:

Beech Aircraft Corporation: Docket No. 96-CE-11-AD. Supersedes AD 
92-27-10, Amendment 39-8444.

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

------------------------------------------------------------------------
            Models                             Serial No.               
------------------------------------------------------------------------
65-90, 65-A90, B90, C90, and   LJ-1 through LJ-1307.                    
 C90A.                                                                  
65-A90-1 (U-21A).............  LM-1 through LM-63, LM-65, LM-67 through 
                                LM-69, LM-71 through LM-99, and LM- 112 
                                through LM-114.                         
65-A90-1 (JU-21A)............  LM-64, LM-66, and LM-70.                 
65-A90-1 (RU-21D)............  LM-100, LM-102 through LM-106, and LM-116
                                through LM-124.                         
65-A90-1 (RU-21H)............  LM-101 LM-107, LM-115, LM-125, LM-127, LM-
                                128, LM-129, LM-132, LM-133, LM- 136, LM-
                                137, and LM-138.                        
65-A90-1 (RU-21A)............  LM-108 through LM-111.                   
65-A90-1 (U-21G).............  LM-126, LM-130, LM-131, LM- 134, LM-135, 
                                and LM-139 through LM-141.              
65-A90-2 (RU-21B)............  LS-1, LS-2, and LS-3.                    
65-A90-3 (RU-21C)............  LT-1 and LT-2.                           
65-A90-4 (RU-21E)............  LU-1, LU-3, LU-4, LU-7, LU-8, and LU-14. 
65-A90-4 (RU-21H)............  LU-2, LU-5, LU-6, LU-9, LU-10 through LU-
                                13, and LU-15.                          
E90..........................  LW-1 through LW-347.                     
H90 (T-44A)..................  LL-1 through LL-61.                      
F90..........................  LA-2 through LA-236.                     

[[Page 29996]]

                                                                        
99, 99A, A99A, B99, and C99..  U-1 through U-239.                       
100 and A100.................  B-1 through B-94 and B-100 through B-247.
A100 (U-21F).................  B-95 through B-99.                       
A100-1 (U-21J)...............  BB-3, BB-4, and BB-5.                    
B100.........................  BE-1 through BE-137.                     
200 and B200.................  BB-2 and BB-6 through BB-1440.           
200C and B200C...............  BL-1 through BL-72 and BL-124 through BL-
                                137.                                    
200CT and B200CT.............  BN-1 through BN-4.                       
200T and B200T...............  BT-1 through BT-34.                      
A200 (C-12A, C-12C)..........  BD-1 through BD-30, and BC-1 through BC- 
                                75.                                     
A200 (UC-12B)................  BJ-1 through BJ-66.                      
A200CT (C-12D)...............  BP-1, BP-22, and BP-24 through BP-51.    
A200CT(FWD-12D)..............  BP-7 through BP-11.                      
A200CT (RC-12D)..............  GR-1 through GR-13.                      
A200CT (C-12F)...............  BP-52 through BP-63.                     
A200CT (RC-12G)..............  FC-1, FC-2, and FC-3.                    
A200CT (RC-12H)..............  GR-14 through GR-19.                     
A200CT (RC-12K)..............  FE-1 through FE-23.                      
B200C (C-12F)................  BL-73 through BL-112, and BL-118 through 
                                BL-123.                                 
B200C (UC-12F)...............  BU-1 through BU-10.                      
B200C (RC-12F)...............  BU-11 and BU-12.                         
B200C (UC-12M)...............  BV-1 through BV-10.                      
B200C (RC-12M)...............  BV-11 and BV-12.                         
B200CT (FWD-12D).............  FG-1 and FG-2.                           
B200CT (C-12F)...............  BP-64 through BP-71.                     
1900.........................  UA-1, UA-2, and UA-3.                    
1900C........................  UB-1 through UB-74, and UC-1 through UC- 
                                174.                                    
1900C (C-12).................  UD-1 through UD-6.                       
1900D........................  UE-1 through UE-17.                      
------------------------------------------------------------------------



    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 150 hours time-in-
service after the effective date of this AD, unless already 
accomplished.

    To prevent inadvertent movement of the pilot or copilot chair, 
which could result in loss of control of the airplane if it occurs 
during a critical flight maneuver, accomplish the following:
    (a) Inspect the pilot and copilot chairs to ensure that the 
locking pins will fully engage in the seat tracks in accordance with 
the ACCOMPLISHMENT INSTRUCTIONS section of Beech Service Bulletin 
(SB) No. 2444, Revision II, dated May 1995. Prior to further flight, 
modify any chair where any locking pin fails to fully engage or is 
misaligned in accordance with the maintenance manual as specified in 
Beech SB No. 2444, Revision II, dated May 1995.
    (b) The inspection and modification required by paragraph (a) of 
this AD are still mandatory even if the actions were previously 
accomplished in accordance with Beech SB No. 2444, dated April 1992, 
or Beech SB No. 2444, Revision I, dated September 1992.
    (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. Alternative methods of compliance approved 
in accordance with AD 92-27-10 (superseded by this action) are not 
considered approved as alternative methods of compliance with this 
AD.
    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) 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.
    (f) This amendment supersedes AD 92-27-10, Amendment 39-8444.

    Issued in Kansas City, Missouri, on June 4, 1996.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-14989 Filed 6-12-96; 8:45 am]
BILLING CODE 4910-13-U