AD 97-23-17

[Federal Register Volume 62, Number 224 (Thursday, November 20, 1997)]
[Rules and Regulations]
[Pages 61908-61910]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-30057]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-CE-05-AD; Amendment 39-10207; AD 97-23-17]
RIN 2120-AA64


Airworthiness Directives; Raytheon Aircraft Company 90, 100, 200, 
and 300 Series Airplanes (Formerly Known as Beech Aircraft Corporation 
90, 100, 200, and 300 Series Airplanes)

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to Raytheon Aircraft Company (Raytheon) 90, 100, 200, and 300 
series airplanes. This action requires inspecting gray, blue, or clear 
Ethylene Vinyl Acetate (EVA) tubing near the co-pilot's foot warmer for 
collapse or deformity. If the tubing is collapsed or deformed, this 
action requires replacing and re-routing the tubing. This EVA tubing is 
used on the pneumatic de-ice indicator lines and the pressurization 
control system pneumatic lines that provide vacuum to the outflow 
safety valves that depressurize the airplane. This action is the result 
of several reports of collapsed EVA tubing. The actions specified by 
this AD are intended to prevent a loss of vacuum to depressurize the 
airplane cabin, which could result in personal injury to the door 
operator; and to prevent malfunction of the de-ice indicator system, 
which could cause the pilot to immediately exit icing conditions.

DATES: Effective December 29, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 29, 1997.

ADDRESSES: Service information that applies to this AD may be obtained 
from 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 Regional Counsel, 
Attention: Rules Docket 97-CE-05-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: Mike Imbler, Aerospace Engineer, FAA, 
Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, 
Mid-

[[Page 61909]]

Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4147, 
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, 100, 
200, and 300 series airplanes was published in the Federal Register on 
May 13, 1997, (62 FR 26261). The action proposed to require inspecting 
the condition and proper routing of the gray, blue, or clear pneumatic 
pressurization control system tubes and the de-ice indicator pneumatic 
tubing located forward of the co-pilot's right outboard rudder pedal. 
If either tube is deformed or collapsed, the proposed action would 
require replacing the damaged section of tube with new nylon tubing, 
then re-routing and securing the tubing using aluminum tubing and hose 
clamps. If there is no evidence of damage to the tubing, the proposed 
action would only require re-routing and securing the tubing to ensure 
that it is at least 8 inches away from the discharge opening of the co-
pilot's foot warmer outlet. Accomplishment of the proposed action would 
be in accordance with Raytheon Aircraft Company Mandatory Service 
Bulletin No. 2676, Issued: January 1997.
    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 2,515 airplanes in the U.S. registry will be 
affected by this AD; that it would take approximately 6 workhours per 
airplane to accomplish the inspection, repair, and re-routing of the 
tubing; and that the average labor rate is approximately $60 an hour. 
Parts would be covered under the manufacturer's warranty credit 
program. Based on these figures, the total cost impact of this AD on 
U.S. operators is estimated to be $905,400 or $360 per airplane. The 
FAA has no way to determine the number of owners/operators of the 
affected airplanes who may have already accomplished this action.

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 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

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

97-23-17.--Raytheon Aircraft Company: Amendment 39-10207; Docket No. 
97-CE-05-AD.

    Applicability: The following models and serial numbered 
airplanes, certificated in any category:

------------------------------------------------------------------------
                  Models                             Serial Nos.        
------------------------------------------------------------------------
C90 and C90A..............................  LJ-683 through LJ-1463.     
E90.......................................  LW-177 through LW-347.      
F90.......................................  LA-1 through LA-236.        
H90.......................................  LL-1 through LL-61.         
A100......................................  B-228 through B-247.        
B100......................................  BE-6 through BE-137.        
200 and B200..............................  BB-114 through BB-1553.     
200C and B200C............................  BL-1 through BL-72 and BL-  
                                             124 through BL-140.        
200CT and B200CT..........................  BN-1 through BN-4.          
200T and B200T............................  BT-1 through BT-38.         
300.......................................  FA-1 through FA-230 and FF-1
                                             through FF-19.             
B300......................................  FL-1 through FL-154.        
B300C.....................................  FM-1 through FM-9 and FN-1. 
A200 (C-12C)..............................  BC-19 through BC-75 and BD- 
                                             15 through BD-30.          
A200C (UC-12B)............................  BJ-1 through BJ-66.         
A200CT (C-12D/F)..........................  BP-1, BP-22, and BP-24      
                                             through BP-63.             
A200CT (FWC-12D)..........................  BP-7 through BP-11.         
A200CT (RC-12D)...........................  GR-1 through GR-13.         
A200CT (RC-12H)...........................  GR-14 through GR-19.        
A200CT (RC-12G)...........................  FC-1 through FC-3.          
A200CT (RC-12K)...........................  FE-1 through FE-9.          
A200CT (RC-12N)...........................  FE-10 through FE-31.        
A200CT (RC-12P)...........................  FE-33 and FE-35.            
A200CT (RC-12Q)...........................  FE-32, FE-34, and FE-36.    
B200C (C-12F).............................  BL-73 through BL-112, BL-118
                                             through BL-123, and BP-64  
                                             through BP-71.             
B200C (C-12R).............................  BW-1 through BW-29.         
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 (FWC-12D)..........................  FG-1 and FG-2.              
------------------------------------------------------------------------

    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 (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.


[[Page 61910]]


    Compliance: Required within the next 200 hours time-in-service 
(TIS) after the effective date of this AD, unless already 
accomplished.
    To prevent a loss of vacuum to depressurize the airplane cabin, 
which could result in personal injury to the door operator; and to 
prevent malfunction of the de-ice indicator system which could cause 
the pilot to unnecessarily exit icing conditions, accomplish the 
following:
    (a) Inspect for collapse, deformation, and proper routing of the 
gray, blue, or clear pneumatic pressurization control system tubes 
and the de-ice indicator pneumatic tubing located forward of the co-
pilot's right outboard rudder pedal in accordance with the 
ACCOMPLISHMENT INSTRUCTIONS section and Figure 1 of the Raytheon 
Aircraft Company (Raytheon) Mandatory Service Bulletin (SB) No. 
2676, Issued: January 1997.
    (b) If any of this tubing is deformed or collapsed, prior to 
further flight, replace the damaged section of tube with new nylon 
tubing, then use aluminum tubing and hose clamps to secure and re-
route the tubing at least 8 inches away from the discharge opening 
of the co-pilot's foot warmer outlet in accordance with the 
ACCOMPLISHMENT INSTRUCTIONS section and Figure 2 of the Raytheon 
Mandatory SB No. 2676, Issued: January 1997.
    (c) If there is no evidence of damage to the tubing, prior to 
further flight, re-route and secure the tubing as specified in 
paragraph (b) of this AD in accordance with the ACCOMPLISHMENT 
INSTRUCTIONS section of the Raytheon Mandatory SB No. 2676, Issued: 
January 1997.
    (d) 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.
    (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, 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 Aircraft Certification Office.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from Wichita Aircraft Certification Office.

    (f) The inspections, modifications, and replacements required by 
this AD shall be done in accordance Raytheon Aircraft Company 
Mandatory Service Bulletin No. 2676, Issued: January 1997. 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 Raytheon Aircraft Company, P.O. Box 
85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, 
Central Region, Office of the Regional 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.
    (g) This amendment (39-10207) becomes effective on December 29, 
1997.

    Issued in Kansas City, Missouri, on November 7, 1997.
Larry D. Malir,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-30057 Filed 11-19-97; 8:45 am]
BILLING CODE 4910-13-U