[Federal Register Volume 60, Number 121 (Friday, June 23, 1995)]
[Proposed Rules]
[Pages 32628-32630]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-15462]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 93-CE-21-AD]
Airworthiness Directives; Fairchild Aircraft SA226 and SA227
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to revise 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 spar straps if the wing skin is found
cracked; and, if any crack is found in the spar straps, repairing the
spar straps and modifying the wing skin. That AD references an
incorrect dye penetrant inspection when the wing skin is found cracked.
This action would maintain the requirements of AD 94-07-10, but would
incorporate the correct dye penetrant inspection for when the wing skin
is found cracked. The actions specified by the proposed 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: Comments must be received on or before August 25, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 93-CE-21-AD, Room 1558, 601 E.
12th Street, Kansas City, Missouri 64106. Comments may be inspected at
this location between 8 a.m. and 4 p.m., Monday through Friday,
holidays excepted.
Service information that applies to the proposed AD may be obtained
from Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-
0490; telephone (512) 824-9421. This information also may be examined
at the Rules Docket at the address above.
FOR FURTHER INFORMATION CONTACT: Mr. Hung Viet Nguyen, Aerospace
Engineer, FAA, Airplane Certification Office, 2601
[[Page 32629]] Meacham Boulevard, Fort Worth, Texas 76137-0150;
telephone (817) 222-5155; facsimile (817) 222-5960.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications should identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report that summarizes each FAA- public contact concerned
with the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 93-CE-21-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Central Region, Office of the Assistant Chief Counsel,
Attention: Rules Docket No. 93-CE-21-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Discussion
AD 94-07-10, Amendment 39-8868 (59 FR 15329; April 1, 1994),
currently requires the following on certain Fairchild Aircraft SA226
and SA227 series airplanes: repetitively inspecting (visually) the wing
skin for cracks; dye penetrant inspecting the spar straps if the wing
skin is found cracked; and, if any crack is found in the spar straps,
repairing the spar straps and modifying the wing skin. That AD also
provides the option of modifying the wing skin as terminating action
for the repetitive inspections. Accomplishment of the required actions
would be in accordance with the following service bulletins (SB), 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);
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).
Since issuing that AD, the FAA has received reports that AD 94-07-
10 references an incorrect dye penetrant inspection in the applicable
service information. The FAA has determined that reference to this dye
penetrant inspection should be corrected and incorporated into the AD.
After examining the circumstances and reviewing all available
information related to the incidents described above, the FAA has
determined that AD action should be taken 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.
Since an unsafe condition has been identified that is likely to
exist or develop in other Fairchild Aircraft SA226 and SA227 series
airplanes of the same type design, the proposed AD would revise AD 94-
07-10 to require the same repetitive visual inspections, but require
the dye penetrant inspection in accordance with the correct portion of
the ACCOMPLISHMENT INSTRUCTIONS section of the above-referenced service
bulletins, as applicable.
The FAA estimates that 776 airplanes in the U.S. registry would be
affected by the proposed AD, that it would take approximately 1
workhour per airplane to accomplish the proposed 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 spar strap that would be required if the wing skin is found
cracked, nor does it include the cost of the wing skin modification or
the repetitive inspections. The optional modification would terminate
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 proposed actions impose the same cost impact upon
U.S. operators as is already required by AD 94-07-10.
The regulations proposed herein would 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
proposal would 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) if promulgated,
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 draft regulatory evaluation
prepared for this action has been placed 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, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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 94-07-10, Amendment 39-
8868 (59 FR 15329; April 1, 1994), and adding a new AD to read as
follows:
Fairchild Aircraft: 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:
[[Page 32630]]
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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 use the authority
provided in paragraph (e) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition, or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
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), (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, and if no cracks are found, continue to reinspect at
intervals not to exceed 150 hours TIS; or
(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). 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) All persons affected by this directive may obtain copies of
the documents referred to herein upon request to Fairchild Aircraft,
P.O. Box 790490, San Antonio, Texas 78279-0490; or may examine these
documents at the FAA, Central Region, Office of the Assistant Chief
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.
(g) This amendment revises AD 94-07-10, Amendment 39-8868.
Issued in Kansas City, Missouri, on June 19, 1995.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-15462 Filed 6-22-95; 8:45 am]
BILLING CODE 4910-13-U
