[Federal Register Volume 61, Number 31 (Wednesday, February 14, 1996)]
[Rules and Regulations]
[Pages 5675-5677]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-3286]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 93-CE-21-AD; Amendment 39-9516; AD 94-07-10 R1]
Airworthiness Directives; Fairchild Aircraft SA226 and SA227
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment revises AD 94-07-10, which currently requires
the following on Fairchild Aircraft SA226 and SA227 series airplanes:
Repetitively inspecting (visually) the wing skin for cracks; dye
penetrant inspecting the rib straps if the wing skin is found cracked;
and, if any crack is found in the rib straps, repairing the rib straps
and modifying the wing skin. That AD references an incorrect dye
penetrant inspection when the wing skin is found cracked. This action
maintains the requirements of AD 94-07-10, but incorporates reference
to the correct dye penetrant inspection for when the wing skin is found
cracked. The actions specified by this AD are intended to prevent
failure of the wing skin at the top aft outboard corner of the battery
box, which could result in structural damage to the wing.
DATES: Effective March 25, 1996.
The incorporation by reference of certain publications listed in
the regulations was previously approved by the Director of the Federal
Register as of May 27, 1994.
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, Attention: Rules Docket 93-CE-21-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, Airplane Certification Office, 2601 Meacham Boulevard,
Fort Worth, Texas 76193-0150; telephone (817) 222-5155; facsimile (817)
222-5960.
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 Fairchild Aircraft SA226 and SA227 series airplanes was published in
the Federal Register on June 23, 1995 (60 FR 32628). The action
proposed to revise AD 94-07-10 to retain the requirement of
repetitively inspecting the wing skin for cracks, and would maintain
the dye penetrant inspection requirement but require it in accordance
with the correct portion of the ACCOMPLISHMENT INSTRUCTIONS section of
the applicable service bulletin. This action also proposed to maintain
the option of modifying the wing skin as terminating action for the
repetitive inspections. Accomplishment of the proposed actions would be
in accordance with one of the following, as applicable:
--Fairchild Service Bulletin (SB) 226-57-018, Issued: January 28, 1993,
Revised: June 3, 1993 (pages 4 through 11 and 13 through 15), Revised:
July 1, 1993 (page 12) and Revised: October 25, 1993 (pages 1 through
3);
[[Page 5676]]
--Fairchild SB 227-57-005, Issued: December 21, 1992, Revised: June 3,
1993 (pages 2 through 11 and 13 through 15), and Revised: July 1, 1993
(pages 1 and 12); or
--Fairchild Aircraft SB CC7-57-002, Issued: January 28, 1993, Revised:
June 3, 1993 (pages 2 through 11 and 13 through 15), and Revised: July
1, 1993 (pages 1 and 12).
Interested persons have been afforded an opportunity to participate
in the making of this amendment. One comment was received in favor of
the proposal and no comments were received regarding the FAA's
determination of the cost to the public.
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.
The FAA estimates that 776 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 1 workhour per
airplane to accomplish the required visual inspection of the upper wing
skin on both wings, and that the average labor rate is approximately
$60 an hour. Based on these figures, the total cost impact of the AD on
U.S. operators is estimated to be $46,560. This figure does not include
the cost of any dye penetrant inspections of the rib strap that will be
required if the wing skin is found cracked, and it does not include the
cost of the repetitive inspections or the optional modification.
Incorporating the optional modification terminates the need for the
repetitive inspection requirement. The figure above is based upon the
assumption that no affected airplane owner/operator has accomplished
this inspection-terminating modification.
In addition, the actions required by this AD impose the same cost
impact upon U.S. operators as is already required by AD 94-07-10.
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 removing Airworthiness Directive
(AD) 94-07-10, Amendment 39-8868 (59 FR 15329; April 1, 1994), and by
adding a new AD to read as follows:
94-07-10 R1 Fairchild Aircraft: Amendment 39-9516; Docket No. 93-CE-
21-AD. Revises AD 94-07-10, Amendment 39-8868.
Applicability: The following model and serial number airplanes,
certificated in any category:
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Model Serial Nos.
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SA226-T............................... T201 through T275, and T277
through T291.
SA226-T(B)............................ T(B)276, and T(B)292 through
T(B)417.
SA226-AT.............................. AT001 through AT074.
SA226-TC.............................. TC201 through TC419.
SA227-TT.............................. TT421 through TT541.
SA227-AT.............................. AT423 through AT631, and AT695.
SA227-AC.............................. AC406, AC415, AC416, and AC420
through AC789.
SA227-BC.............................. BC420 through BC789.
SA227-CC.............................. CC784, and CC790 through CC822.
SA227-DC.............................. DC784, and DC790 through DC822.
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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 initially upon the accumulation of
2,500 hours time-in-service (TIS) or within the next 100 hours TIS
after the effective date of this AD, whichever occurs later, unless
already accomplished (compliance with AD 94-07-10), and thereafter
as indicated in the body of the AD.
To prevent failure of the wing skin at the top aft outboard
corner of the battery box, which could result in structural damage
to the wing, accomplish the following:
Note 2: The paragraph structure of this AD is as follows:
Level 1: (a), (b), (c), etc.
Level 2: (1), (2), (3), etc.
Level 3: (i), (ii), (iii), etc.
Level 2 and Level 3 structures are designations of the Level 1
paragraph they immediately follow.
(a) Visually inspect the right and left upper wing skin by the
top aft outboard corner of the battery box for cracks in accordance
with Figure 1 and the ACCOMPLISHMENT INSTRUCTIONS, A. Inspection,
section of whichever of the following is applicable:
(1) Fairchild Service Bulletin (SB) 226-57-018, Issued: January
28, 1993, Revised: June 3, 1993 (pages 4 through 11 and 13 through
15), Revised: July 1, 1993 (page 12) and Revised: October 25, 1993
(pages 1 through 3);
(2) Fairchild SB 227-57-005, Issued: December 21, 1992, Revised:
June 3, 1993 (pages 2 through 11 and 13 through 15), and Revised:
July 1, 1993 (pages 1 and 12); or
(3) Fairchild Aircraft SB CC7-57-002, Issued: January 28, 1993,
Revised: June 3, 1993 (pages 2 through 11 and 13 through 15), and
Revised: July 1, 1993 (pages 1 and 12).
(b) If cracks are not found during the visual inspection
required by paragraph (a) of this AD, within 500 hours TIS after
this initial visual inspection, accomplish one of the following:
(1) Reinspect the right and left upper wing skin by the top aft
outboard corner of the battery box for cracks in accordance with
Figure 1 and the ACCOMPLISHMENT INSTRUCTIONS, A. Inspection, section
of the applicable service information presented in paragraphs
(a)(1), (a)(2), and (a)(3) of this AD, and reinspect thereafter at
intervals not to exceed 500 hours TIS; or
(2) Modify the upper wing skin in accordance with the
ACCOMPLISHMENT INSTRUCTIONS, B. Removal and C. Installation, section
of the service information referenced in paragraphs (a)(1),
[[Page 5677]]
(a)(2), or (a)(3) of this AD, as applicable. Accomplishing this
modification terminates the repetitive visual inspections that are
specified in paragraph (b)(1) of this AD, and the modification may
be accomplished at any time to eliminate this repetitive inspection
requirement.
(c) If cracks are found during the inspection required by
paragraph (a) of this AD, prior to further flight, dye penetrant
inspect the 27-31130 straps in the wheel wells as specified in the
ACCOMPLISHMENT INSTRUCTIONS, A. Inspection section, paragraph
(1)(b), of the service information referenced in paragraphs (a)(1),
(a)(2), or (a)(3) of this AD, as applicable.
(1) If cracks are found in either of the 27-31130 straps during
the inspection required by paragraph (c) of this AD, prior to
further flight, accomplish the following:
(i) Repair the 27-31130 strap in accordance with a scheme
obtained from the manufacturer through the Fort Worth Airplane
Certification Office (ACO) at the address specified in paragraph (e)
of this AD; and
(ii) Modify the upper wing skin in accordance with the
ACCOMPLISHMENT INSTRUCTIONS, B. Removal and C. Installation, section
of the service information referenced in paragraphs (a)(1), (a)(2),
or (a)(3) of this AD, as applicable.
(2) If no cracks are found in either of the 27-31130 straps,
within 150 hours TIS after the initial dye penetrant inspection
required by paragraph (c) of this AD, accomplish one of the
following:
(i) Reinspect (dye penetrant) the 27-31130 straps in the wheel
well for cracks as specified in the ACCOMPLISHMENT INSTRUCTIONS, A.
Inspection section, paragraph (1)(b), of the service information
referenced in paragraphs (a)(1), (a)(2), or (a)(3) of this AD, as
applicable. Continue to reinspect at intervals not to exceed 150
hours TIS provided no cracks are found, and repair and modify as
specified in paragraphs (c)(1) and (c)(2) of this AD if any cracks
are found.
(ii) Modify the upper wing skin in accordance with the
ACCOMPLISHMENT INSTRUCTIONS, B. Removal and C. Installation, section
of the service information referenced in paragraphs (a)(1), (a)(2),
or (a)(3) of this AD, as applicable. Accomplishing this modification
terminates the repetitive dye penetrant inspections that are
specified in paragraph (c)(2)(i) of this AD, and the modification
may be accomplished at any time to eliminate this repetitive
inspection requirement.
Note 3: Certain Limited Approved Repair (LAR) and Approved
Repair Procedure (ARP) documents issued by Fairchild Aircraft
specify procedures for accomplishing the same modification
referenced in paragraphs (b)(2), (c)(1)(ii), and (c)(2)(ii) of this
AD. Check with the Fort Worth ACO at the address presented in
paragraph (e) of this AD to find out which LAR's and ARP's are
considered ``unless already accomplished'' as they relate to this
AD.
(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 times that provides an equivalent
level of safety may be approved by the Manager, Fort Worth ACO, FAA,
2601 Meacham Boulevard, Fort Worth, Texas 76137-0150. 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 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Fort Worth ACO.
(f) Alternative methods of compliance approved in accordance
with AD 94-07-10 (revised by this action) are considered approved as
alternative methods of compliance with this AD.
(g) The inspections, possible repair, and optional modification
required by this AD shall be done in accordance with Fairchild
Service Bulletin 226-57-018, Issued: January 28, 1993, Revised: June
3, 1993 (pages 4 through 11 and 13 through 15), Revised: July 1,
1993 (page 12) and Revised: October 25, 1993 (pages 1 through 3);
Fairchild Service Bulletin 227-57-005, Issued: December 21, 1992,
Revised: June 3, 1993 (pages 2 through 11 and 13 through 15), and
Revised: July 1, 1993 (pages 1 and 12); or Fairchild Aircraft
Service Bulletin CC7-57-002, Issued: January 28, 1993, Revised: June
3, 1993 (pages 2 through 11 and 13 through 15), and Revised: July 1,
1993 (pages 1 and 12), as applicable. This incorporation by
reference was previously 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., 7th Floor, suite
700, Washington, DC.
(h) This amendment (39-9516) revises AD 94-07-10, Amendment 39-
8868.
(i) This amendment (39-9516) becomes effective on March 25,
1996.
Issued in Kansas City, Missouri, on February 7, 1996.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 96-3286 Filed 2-13-96; 8:45 am]
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