[Federal Register Volume 62, Number 49 (Thursday, March 13, 1997)]
[Rules and Regulations]
[Pages 11764-11766]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-6255]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 96-CE-11-AD; Amendment 39-9963; AD 97-06-06]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Company (Formerly 
Beech Aircraft Corporation) 90, 99, 100, 200, and 1900 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes 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 Raytheon 
Aircraft Company (Raytheon) 90, 99, 100, 200, and 1900 series airplanes 
(formerly referred to as Beech 90, 99, 100, 200, and 1900 series 
airplanes), and modifying any chair where the locking pin fails to 
fully engage or is misaligned. AD 92-27-10 resulted from reports of 
pilot and copilot chair locking pin malfunctions. Since issuance of 
that AD, the Federal Aviation Administration (FAA) has determined that 
additional airplanes should be subject to the pilot and copilot chair 
locking pin inspection and possible modification, and that the 
inspection should be accomplished in accordance with revised 
procedures. This AD retains the inspection and possible modification 
requirements of AD 92-27-10; incorporates additional airplanes into the 
applicability over that included in AD 92-27-10; and requires the 
inspection in accordance with revised service information. The actions 
specified by this 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: Effective May 9, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 9, 1997.


[[Page 11765]]


ADDRESSES: Service information that applies to this AD may be obtained 
from the Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-
0085. This information may also be examined at 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; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, Washington, 
DC.

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:

Events Leading to the Issuance of This AD

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to Raytheon 90, 99, 100, 
200, and 1900 series airplanes (formerly referred to as Beech 90, 99, 
100, 200, and 1900 series airplanes) was published in the Federal 
Register as a notice of proposed rulemaking (NPRM) on June 13, 1996 (61 
FR 29994). The NPRM proposed to 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 the 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.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposed rule or the FAA's determination of the cost to the public.

The FAA's Determination

    After careful review of all available information related to the 
subject presented above, the FAA has determined that air safety and the 
public interest require the adoption of the rule as proposed except for 
minor editorial corrections. The FAA has determined that these minor 
corrections will not change the meaning of the AD and will not add any 
additional burden upon the public than was already proposed.

Cost Impact

    The FAA estimates that 4,971 airplanes in the U.S. registry will be 
affected by this AD, that it will take approximately 1 workhour per 
airplane to accomplish the required 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 this 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 will take approximately 2 workhours per airplane at an 
average labor rate of $60 per hour ($120 per airplane).

Regulatory Impact

    The regulations adopted herein will 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 final 
rule does 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) 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 final evaluation prepared for this 
action is contained 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends 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), 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:

97-06-06  Raytheon Aircraft Company (formerly Beech Aircraft 
Corporation): Amendment 39-9963; 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 Nos.          
------------------------------------------------------------------------
65-90, 65-A90, B90, C90, and C90A......  LJ-1 through LJ-1307.          
65-A90-1 (U-21A).......................  LM-1 through LM-63, 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.           

[[Page 11766]]

                                                                        
H90 (T-44A)............................  LL-1 through LL-61.            
F90....................................  LA-2 through LA-236.           
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.                         
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 assure 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 the 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 possible modification required by 
paragraph (a) of this AD is 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) The inspection required by this AD shall be done in 
accordance with Beech Service Bulletin No. 2444, Revision II, dated 
May 1995. This incorporation by reference was approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51. Copies may be obtained from the Raytheon Aircraft 
Company, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be 
inspected at the FAA, Central Region, Office of the Assistant Chief 
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.
    (f) This amendment (39-9963) supersedes AD 92-27-10, Amendment 
39-8444.
    (f) This amendment (39-9963) becomes effective on May 9, 1997.

    Issued in Kansas City, Missouri, on March 5, 1997.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 97-6255 Filed 3-12-97; 8:45 am]
BILLING CODE 4910-13-U