[Federal Register Volume 62, Number 88 (Wednesday, May 7, 1997)]
[Rules and Regulations]
[Pages 24809-24810]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-11895]
[[Page 24809]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-CE-89-AD; Amendment 39-10005; AD 97-09-09]
RIN 2120-AA64
Airworthiness Directives; Raytheon Aircraft Company (Formerly
Beech Aircraft Corporation) Models 58P and 58PA 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 (formerly Beech Aircraft
Corporation) Models 58P and 58PA airplanes. This action requires
inspecting for cracks in the right-hand (RH) upper and lower longeron
near the second RH cabin window, inspecting for missing rivets in the
cabin structure (longeron) adjacent to and aft of the second RH cabin
window, repairing any cracked structure or reinforcing the longeron if
it is not cracked, and installing rivets, if missing. Reports of cracks
in the upper and lower longeron and missing rivets that are supposed to
secure the frame, splice, and longeron together prompted this action.
The actions specified by this AD are intended to prevent structural
cracking to the cabin caused by missing rivets, which if not corrected,
could cause decompression injuries to passengers, structural failure of
the fuselage, and loss of the airplane.
DATES: Effective June 30, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 30, 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 Assistant Chief
Counsel, Attention: Rules Docket 95-CE-89-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: David Ostrodka, Aerospace Engineer,
FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room
100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946-
4129, 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 Aircraft
Company Models 58P and 58PA airplanes was published in the Federal
Register on December 2, 1996 (61 FR 63762). The action proposed to
require (1) inspecting for cracks on the right-hand (RH) lower longeron
between two doublers adjacent to the lower aft side of the RH second
cabin window, (2) repairing any cracks found, (3) reinforcing the
longeron if no cracks are found, (4) inspecting for cracks and missing
rivets in the upper longeron adjacent to and aft of the second RH cabin
window, and (5) repairing any cracks and installing any rivets, if
missing.
Accomplishment of the inspection, repair, and reinforcement would
be in accordance with Beechcraft Service Bulletin (SB) No. 2630,
Issued: November, 1995, and Raytheon Aircraft Mandatory SB No. 2691,
Rev. 1, Issued: June, 1996; Revised: October, 1996.
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.
After publication of the Supplemental NPRM, the estimated costs of the
proposed actions were changed to reflect a more accurate amount for
labor and parts of the initial inspection. The cost estimate increased
from approximately $300 to approximately $648 per airplane, which is a
difference of about $250 per airplane. There is no change to the
proposed AD, only a more accurate reflection of the cost estimate to
accomplish the actions proposed in the Supplemental NPRM.
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 386 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 9 workhours (3
workhours for the inspection and 6 workhours to accomplish the
reinforcement) to accomplish the action and that the average labor rate
is approximately $60 an hour. Parts to accomplish the reinforcement
cost $100 per airplane. In estimating the total cost impact of this AD
on U.S. operators, the FAA is presuming that no cracked longeron will
be found, no missing rivets will be found, and the reinforcement will
need to be incorporated on each effected airplane. Based on these
figures, the total cost impact of this AD on U.S. operators is
estimated to be $247,040 or $648 per airplane.
If, during the inspection, cracks are found and rivets are missing,
the estimated costs for accomplishing the following actions will be:
--2 workhours to install rivets at an estimated cost of $125 per
airplane ($120 for labor and $5 for rivets),
--8 workhours to repair any crack in the designated area of the RH
upper longeron at an estimated cost of $675 per airplane ($480 for
labor and $195 for parts),
--6 workhours to re-reinforce the RH lower longeron at an estimated
cost of $460 per airplane ($360 for labor and $100 for parts), or
--16 workhours to repair any crack found in the RH lower longeron
at an estimated cost of $2,060 per airplane ($960 for labor and $1,100
for parts).
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.
[[Page 24810]]
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:
97-09-09. Raytheon Aircraft Company: Amendment No. 39-10005; Docket
No. 95-CE-89-AD.
Applicability: Models 58P and 58PA airplanes, having the
following serial numbers, and certificated in any category:
Serial Numbers Listed in Beech Service Bulletin (SB) No. 2630
TJ-2 through TJ-177
TJ-179
TJ-181 through TJ-212
TJ-214 through TJ-270
TJ-272 through TJ-283
TJ-285 through TJ-288
TJ-290 through TJ-313
TJ-315 through TJ-321
TJ-323, TJ-324
TJ-326 through TJ-368, and
TJ-370 through TJ-497
Serial Numbers Listed in Raytheon SB No. 2691
TJ-2 through TJ-121
TJ-123 through TJ 394
TJ-396 through TJ-497
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 100 hours time-in-service
(TIS) after the effective date of this AD, unless already
accomplished:
To prevent structural cracking to the cabin caused by missing
rivets, which, if not detected and corrected, could cause
decompression injuries to passengers, structural failure of the
fuselage, and loss of the airplane, accomplish the following:
(a) Inspect the cabin window upper longeron (next to the upper
aft splice) between the second and third right-hand (RH) cabin side
windows for cracks and missing rivets in accordance with the
ACCOMPLISHMENT INSTRUCTIONS section of Beechcraft Mandatory (Beech)
Service Bulletin (SB) No. 2630, Issued: November 1995.
(1) If cracks are found in the upper longeron, prior to further
flight, repair the cracks in accordance with the ACCOMPLISHMENT
INSTRUCTIONS section of Beech SB No. 2630, Issued: November 1995.
(2) If rivets are found missing, prior to further flight,
install the rivets in accordance with the ACCOMPLISHMENT
INSTRUCTIONS section of Beech SB No. 2630, Issued: November 1995.
(b) Inspect the RH lower longeron between the two doublers
adjacent to the lower aft side of the RH second cabin window for
cracks in accordance with the ACCOMPLISHMENT INSTRUCTIONS section,
PART I of Raytheon Mandatory SB No. 2691, Rev. 1, Issued: June,
1996, Revised: October 1996.
(1) If cracks are found in the RH lower longeron, prior to
further flight, repair and reinforce the cracks in accordance with
the ACCOMPLISHMENT INSTRUCTIONS section, PART II in Raytheon
Mandatory SB No. 2691, Rev. 1, Issued: June, 1996, Revised: October
1996.
(2) If no cracks are found in the RH lower longeron, prior to
further flight, reinforce the longeron in accordance with the
ACCOMPLISHMENT INSTRUCTIONS section, PART III in Raytheon Mandatory
SB No. 2691, Rev. 1, Issued: June, 1996, Revised: October 1996.
(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, 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.
(e) The inspections, installations, repairs, and reinforcements
required by this AD shall be done in accordance with Beechcraft
Service Bulletin No. 2630, Issued: November, 1995, and Raytheon
Aircraft Mandatory Service Bulletin No. 2691, Rev. 1, Issued: June,
1996; Revised: October, 1996. 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
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 (39-10005) becomes effective on June 30,
1997.
Issued in Kansas City, Missouri, on April 30, 1997.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 97-11895 Filed 5-6-97; 8:45 am]
BILLING CODE 4910-13-U
