[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:
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Models Serial Nos.
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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]
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