[Federal Register Volume 60, Number 6 (Tuesday, January 10, 1995)]
[Rules and Regulations]
[Pages 2495-2496]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-517]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 91-CE-12-AD; Amendment 39-9118; AD 95-01- 07]
Airworthiness Directives; Fairchild Aircraft Models SA227-AC and
SA227-AT Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes Airworthiness Directive (AD) 83-12-
01, which currently requires repetitively inspecting the lower wing
skin panel for cracks on certain Fairchild Aircraft Models SA227-AC and
SA227-AT airplanes, and installing wing skin reinforcement doublers if
any wing skin crack is found. The Federal Aviation Administration's
policy on aging commuter-class aircraft is to eliminate, or, in certain
instances, reduce the number of certain repetitive short-interval
inspections when improved parts or modifications are available. This
action requires installing wing skin reinforcement doublers or wing
skin stringer ties as terminating action for the repetitive inspections
that are currently required by AD 83-12-01. The actions specified by
this AD are intended to prevent fatigue failure of the lower wing skin
panels, which could result in loss of control of the airplane.
DATES: Effective February 17, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 17, 1995.
ADDRESSES: Service information that applies to this AD may be obtained
from Fairchild Aircraft, 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 Assistant Chief Counsel, 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, Airplane Certification Office, 2601 Meacham Boulevard,
Fort Worth, Texas 76193-0150; telephone (817) 222-5155; facsimile (817)
222-5959.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an AD that would apply
to certain Fairchild Aircraft Models SA227-AC and SA227-AT airplanes
was published in the Federal Register on March 30, 1994 (59 FR 14797).
The action proposed to supersede AD 83-12- 01 with a new AD that would
(1) retain the requirement of repetitively inspecting the lower wing
skin panel, and installing wing skin reinforcement doublers if any wing
skin crack is found; and (2) require either installing wing skin
reinforcement doublers or wing skin stringer ties as terminating action
for the repetitive inspections. The proposed actions would be
accomplished in accordance with Fairchild SB No. 227-57- 002, Issued:
June 6, 1983, Revised: January 23, 1984.
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 careful review of all available information, 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 nor add any additional burden upon the public than was
already proposed.
This action is based on the FAA's aging commuter-class airplane
policy, which briefly states that owners/operators in commuter service
should incorporate modifications or install improved parts when the
modification or installation would eliminate, or, in certain instances,
reduce a repetitive inspection on a critical structure.
The FAA estimates that 125 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 9 workhours per
airplane to accomplish the required action if reinforcement doublers
were installed (1 workhour/inspection and 8 workhours/modification) or
25 workhours per airplane to accomplish the required action if wing
skin stringer ties were installed (1 workhour/inspection and 24
workhours/modification), and that the average labor rate is
approximately $55 an hour. Parts cost approximately $56 per airplane
for the wing skin reinforcement doublers and $179 per airplane for the
wing skin stringer ties. Based on these figures, the total cost impact
of this AD on U.S. operators is estimated to be either $68,875 for
those airplane operators incorporating the reinforcement doubler
modification or $194,250 for those airplane operators utilizing the
wing skin stringer ties modification. This cost figure is based on the
assumption that no affected airplane owner/operator has accomplished
one of the required inspection-terminating modifications. The figure
does not include repetitive inspection costs. The FAA has no way of
determining how many repetitive inspections each owner/operator may
incur.
The intent of the FAA's aging commuter airplane program is to
ensure safe operation of commuter-class airplanes that are in
commercial service without adversely impacting private operators. Of
the approximately 125 [[Page 2496]] airplanes in the U.S. registry that
will be affected by this AD, approximately 76 are operated in scheduled
passenger service. A significant number of the remaining 49 airplanes
are operated in other forms of air transportation such as air cargo and
air taxi.
This AD allows 500 hours time-in-service (TIS) before mandatory
accomplishment of the design modification. The average utilization of
the fleet for those airplanes in commercial commuter service is
approximately 25 to 50 hours TIS per week. Based on these figures,
operators of commuter-class airplanes involved in commercial operation
will have to accomplish the required modification within 2 to 5
calendar months after this AD becomes effective. For private owners,
who typically operate between 100 to 200 hours TIS per year, this
allows 2 to 5 calendar years before the required modification will be
mandatory.
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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing AD 83-12-01, Amendment 39-
4693, and by adding a new AD to read as follows:
95-01-07 Fairchild Aircraft: Amendment 39-9118; Docket No. 91-CE-12-
AD. Supersedes AD 83-12-01, Amendment 39-4693.
Applicability: The following model and serial number airplanes,
certificated in any category:
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Model Serial Nos.
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SA227-AC............................. 415, 416, and 420 through 554.
SA227-AT............................. 423 through 554.
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Compliance: Required as indicated in the body of this AD, unless
already accomplished.
To prevent fatigue failure of the lower wing skin panels, which
could result in loss of control of the airplane, accomplish the
following:
(a) Within the next 50 hours time-in-service (TIS) after the
effective date of this AD, unless already accomplished (compliance
with AD 83-12-01), dye penetrant inspect the lower wing skin panel
of both wings in the area of Wing Station (WS) 187.0 in accordance
with paragraph IIA of the ACCOMPLISHMENT INSTRUCTIONS section of
Fairchild Service Bulletin (SB) 227-57-002, Issued: June 6, 1983,
Revised: January 23, 1984.
(1) If cracks are found, prior to further flight, install
reinforcement doublers, part number 27K31013-001 LH and 27K31013-002
RH, in accordance with paragraph IIB of the ACCOMPLISHMENT
INSTRUCTIONS section of Fairchild SB 227-57-002, Issued: June 6,
1983, Revised: January 23, 1984.
(2) If no cracks are found, reinspect thereafter at intervals
not to exceed 50 hours TIS until the modification specified in
paragraph (b) of this AD is accomplished.
(b) Within the next 500 hours TIS after the effective date of
this AD, unless already accomplished as specified in paragraph
(a)(1) of this AD, accomplish one of the following on both wings:
(1) Install reinforcement doublers, part number 27K31013-001 LH
and 27K31013-002 RH, in accordance with paragraph IIB of the
ACCOMPLISHMENT INSTRUCTIONS section of Fairchild SB 227-57-002,
Issued: June 6, 1983, Revised: January 23, 1984; or
(2) Install stringer ties, P/N 27-13869, in accordance with
paragraph IIC of the ACCOMPLISHMENT INSTRUCTIONS section of
Fairchild SB 227-57-002, Issued: June 6, 1983, Revised: January 23,
1984.
(c) Incorporating (on both wings) the modification specified in
paragraph (a)(1), (b)(1) or (b)(2) of this AD terminates the
repetitive inspection requirement of this AD.
(d) Special flight permits may be issued in accordance with
Secs. 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 times that provides an equivalent
level of safety may be approved by the Manager, Airplane
Certification Office (ACO), 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 ACO.
Note: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Fort Worth ACO.
(f) The inspections and installation required by this AD shall
be done in accordance with Fairchild Service Bulletin 227-57-002,
Issued: June 6, 1983, Revised: January 23, 1984. 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. 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.
(g) This amendment (39-9118) supersedes AD 83-12-01, Amendment
39-4693.
(h) This amendment (39-9118) becomes effective on February 17,
1995.
Issued in Kansas City, Missouri, on January 4, 1995.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-517 Filed 1-9-95; 8:45 am]
BILLING CODE 4910-13-M
