[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