AD 97-06-06

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.

Final rule

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 Numbers
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
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-1through 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, therequest 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: Informationconcerning 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.

(g) This amendment becomes effective on May 9, 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, 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 themaking 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 ExecutiveOrder 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.

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: