[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