AD 97-23-17

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.

Final rule

97-23-17 RAYTHEON AIRCRAFT COMPANY (formerly Beech Aircraft Corporation): Amendment 39-10207; Docket No. 97-CE-05-AD.

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

Models
Serial Numbers
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 theeffect 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 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.

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 theinspection, 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 asfollows:
Authority: 49 USC 106(g), 40113, 44701.

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