[Federal Register Volume 63, Number 54 (Friday, March 20, 1998)]
[Rules and Regulations]
[Pages 13491-13493]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-6767]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-CE-68-AD; Amendment 39-10403; AD 98-06-25]
RIN 2120-AA64
Airworthiness Directives; Fairchild Aircraft Inc. Models SA226-
AT, SA226-TC, SA227-AC, and SA227-AT 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 Fairchild Aircraft Inc. (Fairchild) Models SA226-AT, SA226-
TC, SA227-AC, and SA227-AT airplanes. This action would require
inspecting the cargo door lower belt frames at the cargo latch
receptacles for cracks in the belt frames, repairing any cracks, and
reinforcing the cargo door lower belt frames by installing doublers.
The AD is the result of a decompression incident during flight caused
by fatigue at the bottom of the cargo door on a Fairchild Model SA226-
TC. The actions specified by this AD are intended to prevent the
failure of the cargo door in flight, which could cause decompression
injuries to passengers and substantial structural damage to the
airplane.
DATES: Effective April 27, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 27, 1998.
ADDRESSES: Service information that applies to this AD may be obtained
from Fairchild Aircraft Inc., P. O. Box 790490, San Antonio, Texas
78279-0490, telephone (210) 824-9421. This information may also be
examined at the Federal Aviation Administration (FAA), Central Region,
Office of the Regional Counsel, Attention: Rules Docket 96-CE-68-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. Hung Viet Nguyen, Aerospace
Engineer, FAA, Fort Worth Airplane Certification Office, 2601 Meacham
Boulevard, Fort Worth, Texas 76193-0150; telephone (817) 222-5155;
facsimile (817) 222-5960.
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 Fairchild Models
SA226-AT, SA226-TC, SA227-AC, and SA227-AT airplanes was published in
the Federal Register on June 4, 1997 (62 FR 30483). The action proposed
would require inspecting the lower belt frames at the cargo latch
receptacles for cracks. If cracks are found, the proposed AD would
require repairing the cracks, prior to further flight, using a repair
scheme provided by the manufacturer through the Ft. Worth Airplane
Certification Office. If no cracks are found, the proposed action would
require reinforcing the cargo door lower belt frames by installing
doublers.
Since Issuance of the Proposed AD
The proposed action required that if cracks were found, the owner/
operator should contact the FAA for an approved repair scheme from
Fairchild Aircraft Inc. Since the Notice of Proposed Rulemaking was
published, Fairchild has developed an FAA-approved repair scheme for
the cargo door belt frames. This repair scheme eliminates the need to
contact the Ft. Worth Airplane Certification Office, which makes it
easier for the owner to fix the airplanes with cracks without waiting
for an approved repair scheme to be developed for each individual
request. In addition to the availability of a repair, the FAA has
clarified the instructions for the inspection of the cargo door belt
frames by referencing certain fuselage stations to be inspected for
cracks. Accomplishment of these actions would be in accordance with the
following service information:
Fairchild Aircraft Corporation SA227 Series Service
Bulletin No. 227-53-003, Issued: January 29, 1986, Revised: February
13, 1986,
Fairchild Aircraft Corporation SA226 Series Service
Bulletin No. 226-53-007, Issued: May 7, 1981, Revised: February 17,
1992,
Fairchild Aircraft SA226/SA227 Structural Repair Manual
(SRM), section 53-90-20, pages 2, 101, 102, 103, and 104; Initial
Issue: March 1, 1983, Revision 24, dated August 27, 1997, or
Fairchild Aircraft Approved Repair Procedure (ARP) 53-30-
9701, dated July 28, 1997.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the following comments.
[[Page 13492]]
Obtaining Repair Approval
Several commenters express concern about access to a repair scheme
and the ability of the FAA to provide a repair scheme outside normal
business hours (8:00 a.m. to 4:30 p.m.). The commenters went on to say
that in many cases, inspections and repairs are made overnight or on
the weekends and waiting on the FAA to provide a repair scheme, on a
case by case basis, could cause the commercial operators flight delays
and cancellations. These commenters request that the FAA approve and
make available a repair scheme prior to the effective date of the
proposed AD. The FAA agrees and has approved a repair scheme developed
by Fairchild Aircraft Inc. The final rule will be changed to reflect
the name and number of these approved repair procedures.
Change of Compliance Time
One commenter requested a change to the compliance times referenced
in paragraphs (a) and (c) of the NPRM. The compliance time proposed was
500 hours time-in-service (TIS) after the effective date of this AD for
the initial inspection for cracks, and if no cracks were found within
the next 500 hours TIS, installing a doubler to the cargo door belt
frames. The commenter wants the initial inspection compliance time
extended to 900 hours TIS after the effective date of this AD, to fit
into the operators' scheduled maintenance to the cargo door belt
frames. The FAA does not agree. The 500 hours TIS compliance time will
assure that the affected airplanes are not flying with cracks in
critical structure. Failure of the cargo door during flight would cause
airplane decompression and possible injury to the passengers, as well
as structural damage to the airplane. The 500 hours TIS initial
inspection is imposed to assure that all the affected airplanes are
checked for cracks in this area within a reasonable amount of time. The
installation of the doubler to strengthen the cargo door belt frames is
not required for another 500 hours TIS, in order to give the owners/
operator an opportunity to schedule this ``down-time'' into their
flight schedules. If no cracks are found in the affected area, the
owners/operators essentially have 1,000 hours total TIS to schedule the
installation of the doublers. The final rule will not change as a
result of this comment.
Crack Limits
Two comments were received regarding the discussion in the NPRM
preamble. The comments addressed the section directed to the
differences between the manufacturer's service bulletin and the
proposed action. The commenters said that the language in the preamble
implied that the manufacturer's service bulletin allowed the operators
to fly with cracks. Although it was not the intent of the FAA to
suggest that the manufacturer allowed flying with cracks, the FAA
agrees that the language in the preamble could be interpreted this way.
The FAA was trying to point out that the compliance times in the
service bulletin were different from those in the proposed action, and
that the service bulletin referred the operator to the manufacturer for
repairs, if cracks of one inch or larger were found. The service
bulletin did not require the operator to contact the manufacturer for
the repair scheme prior to further flight. This language is not
repeated in the final rule, and since a repair scheme is now available
directly from the manufacturer, the only difference between the
manufacturer's service bulletin and the action required by this AD is
the difference in compliance times. The compliance times required by
this AD will take precedence over the compliance times in the Fairchild
service bulletins. The final rule will reflect this change to the
service and repair information in the body of the AD.
The FAA's Determination
After careful review of all available information, including the
service 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 changes and 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 145 airplanes in the U.S. registry are
affected by this AD, that it will take approximately 30 workhours per
airplane to accomplish the initial inspection and installation of the
reinforcing doubler, and that the average labor rate is approximately
$60 an hour. Parts for the installation of the reinforcing doubler cost
approximately $710 per airplane. Based on these figures, the total cost
impact of this AD on U.S. operators is estimated to be $363,950 or
$2,510 per airplane. The FAA has no way to determine the number of
affected airplanes that may have already had this action accomplished.
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 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:
98-06-25 Fairchild Aircraft Inc.: Amendment 39-10403; Docket No. 96-
CE-68-AD.
Applicability: The following models and serial numbered
airplanes, certificated in any category.
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Models Serial numbers
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SA226-AT.......................... AT001 through AT074.
SA226-TC.......................... TC201 through TC419.
[[Page 13493]]
SA227-AC.......................... AC406, AC415, AC416, AC420 through
AC456, AC458 through AC469, and
AC471 through AC478.
SA227-AT.......................... AT423 through AT469.
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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 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 as indicated within the body of this AD,
unless already accomplished.
To prevent failure of the cargo door in flight, which, if not
corrected, could cause decompression injuries to passengers and
substantial structural damage to the airplane, accomplish the
following:
(a) Within the next 500 hours time-in-service (TIS) after the
effective date of this AD, inspect the cargo door lower belt frames
at the cargo latch receptacles for cracks in accordance with Part A
of the ACCOMPLISHMENT INSTRUCTIONS section in Fairchild Aircraft
SA226 Series Service Bulletin (SB) No. 226-53-007, Issued: May 7,
1981; Revised: February 17, 1992, or Fairchild Aircraft SA227 Series
SB No. 227-53-003, Issued: January 29, 1986; Revised: February 13,
1986, whichever is applicable.
(b) If cracks are found during the inspection required in
paragraph (a) of this AD, prior to further flight, accomplish the
following:
(1) For belt frames located at Fuselage Station (F.S.) 438.060
and F.S. 491.060, repair the belt frame by installing angle part
number (P/N) 27-22206-009 or P/N 27-22206-010, in accordance with
the Fairchild Aircraft SA226/227 Structural Repair Manual (SRM),
Section 53-90-20, pages 2, 101, 102, 103, and 104; Initial Issue:
March 1, 1983, Revision 24, dated August 27, 1997; or, Fairchild
Aircraft Approved Repair Procedure (ARP) 53-30-9701, dated July 28,
1997. The reinforcement doublers (P/N 27-22206-007 and -008) are
also needed together with this repair.
(2) For belt frames located at F.S. 454.501, F.S. 455.726, F.S.
473.392, and F.S. 474.657, replace all four belt frames with new
design frames, P/N 27-22207-008, 27-22208-005, 27-22208-005, and 27-
22207-007, respectively, in accordance with the Fairchild Aircraft
SA226/227 SRM, Section 53-90-20, pages 2, 101, 102, 103, and 104;
Initial Issue: March 1, 1983, Revision 24, dated August 27, 1997;
or, Fairchild Aircraft ARP 53-30-9701, dated July 28, 1997. No
reinforcement doublers are needed for these four new design belt
frames.
(c) If no cracks are found in all six belt frames during the
inspection required by paragraph (a) of this AD, install
reinforcement doublers in all six belt frames within 500 hours TIS
from the initial inspection, in accordance with Part B of the
ACCOMPLISHMENT INSTRUCTIONS of Fairchild Aircraft SA226 Series
Service Bulletin (SB) No. 226-53-007, Issued: May 7, 1981; Revised:
February 17, 1992, or Fairchild Aircraft SA227 Series SB No. 227-53-
003, Issued: January 29, 1986; Revised: February 13, 1986, whichever
is applicable.
(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
initial or repetitive compliance time that provides an equivalent
level of safety may be approved by the Manager, Fort Worth Airplane
Certification Office, 2601 Meacham Boulevard, Fort Worth, Texas
76193-0150. The request shall be forwarded through an appropriate
FAA Maintenance Inspector, who may add comments and then send it to
the Manager, Fort Worth Airplane Certification Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Manager, Fort Worth Airplane Certification Office.
(f) The inspections and modifications required by this AD shall
be done in accordance with the following service information:
Fairchild Aircraft Corporation SA227 Series Service
Bulletin No. 227-53-003, Issued: January 29, 1986, Revised: February
13, 1986,
Fairchild Aircraft Corporation SA226 Series Service
Bulletin No. 226-53-007, Issued: May 7, 1981, Revised: February 17,
1992,
Fairchild Aircraft SA226/SA227 Structural Repair Manual
(SRM) section 53-90-20, Initial Issue: March 1, 1983, Revision 24,
dated August 27, 1997, and pages 2, 101, 102, 103, and 104;
Fairchild Aircraft Approved Repair Procedure (ARP) 53-
30-9701, dated July 28, 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 Fairchild Aircraft, P. O. Box
790490, San Antonio, Texas 78279-0490, telephone (210) 824-9421.
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 (39-10403) becomes effective on April 27,
1998.
Issued in Kansas City, Missouri, on March 9, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-6767 Filed 3-19-98; 8:45 am]
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