[Federal Register Volume 62, Number 107 (Wednesday, June 4, 1997)]
[Proposed Rules]
[Pages 30483-30485]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-14544]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-CE-68-AD]
RIN 2120-AA64
Airworthiness Directives; Fairchild Aircraft Incorporated Models
SA226-AT, SA226-TC, SA227-AC, and SA227-AT Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to adopt a new airworthiness directive
(AD) that would apply to certain Fairchild Aircraft Incorporated
(Fairchild) Models SA226-AT, SA226-TC, SA227-AC, and SA227-AT
airplanes. The proposed action would require inspecting the cargo door
lower belt frames at the cargo latch receptacles for cracks in the belt
frames, repairing the cracks, and reinforcing the cargo door lower belt
frames by installing doublers. A decompression incident during flight
caused by fatigue at the bottom of the cargo door on a Fairchild Model
SA226-TC prompted the proposed action. The actions specified by the
proposed 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: Comments must be received on or before August 7, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 96-CE-68-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 (210) 824-9421. This information also may be examined
at the Rules Docket at the address above.
FOR FURTHER INFORMATION CONTACT: 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:
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. 96-CE-68-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. 96-CE-68-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Discussion
In 1995, the FAA received a report on a Fairchild Model SA226-TC
airplane that had a cargo door failure during flight. Upon
investigation, the examiners discovered cracking in the cargo door
lower belt frames. As a result of the incident, the FAA issued AD 95-
18-05 to require replacing the cargo door receptacles to prevent
failure of the cargo door. The FAA has since determined that further AD
action is necessary to address this condition. This proposed AD does
not cancel the actions required in AD 95-18-05.
Relevant Service Information
Fairchild has issued Service Bulletin 227-53-003, Issued: January
29, 1986; Revised: February 13, 1986, and Service
[[Page 30484]]
Bulletin 226-53-007, Issued: May 7, 1981; Revised: February 17, 1992
which specifies inspecting the cargo door belt frames for cracks and
installing reinforcing doublers.
Differences Between Manufacturer's Service Information and the
Proposed Action
Fairchild has suggested different compliance times for repair of
the cracks based on total flight hours of each individual airplane. The
FAA has determined that there should be one compliance time for all
owners/operators of the affected airplanes. These service bulletins
also specify reinforcing the area if cracks found are less than one
inch, and if the cracks are larger than one inch, contact the
manufacturer.
As currently written, the Fairchild service bulletin allows
continued flight if cracks are found in the cargo door lower belt
frames that do not exceed certain limits. The FAA has established a
policy to disallow airplane operation when known cracks exist in
primary structure, unless the ability to sustain ultimate load with
these cracks is proven. The cargo door and the lower belt frame are
considered primary structure, and the FAA has not received any analysis
to prove that ultimate load can be sustained with cracks in this area.
For this reason, the FAA has determined that the crack limits contained
in the service bulletin fall under the policy, and that AD action
should be taken to require immediate replacement of any cracked cargo
door lower belt frames.
The FAA's Determination
After examining the circumstances and reviewing all available
information related to the incident described above, the FAA has
determined that AD action should be taken to prevent the failure of the
cargo door in flight which could cause decompression injuries to
passengers and substantial structural damage to the airplane.
Explanation of the Provisions of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Fairchild Aircraft Models SA226-AT, SA226-TC,
SA227-AC, and SA227-AT airplanes of the same type design, the proposed
AD 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 Airplane Certification
Office. If no cracks are found, the proposed action would require
reinforcing the cargo door lower belt frames by installing doublers.
Cost Impact
The FAA estimates that 145 airplanes in the U.S. registry would be
affected by the proposed AD, that it would take approximately 30
workhours per airplane to accomplish the proposed 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 the proposed 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 have
already accomplished the proposed action.
Regulatory Impact
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 USC 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:
Fairchild Aircraft Incorporated: Docket No. 96-CE-68-AD.
Applicability: The following Models and serial numbered airplanes,
certificated in any category.
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Models Serial Nos.
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SA226-AT............................ AT001 through AT074.
SA226-TC............................ TC201 through TC419.
SA227-AC............................ AC406, AC415, AC416, AC420 through
AC478, except AC457 and AC470.
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 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 the Fairchild Aircraft
(Fairchild) Service Bulletin (SB) No. 226-53-007, Issued: May 7,
1981; Revised: February 17, 1992 or Fairchild SB No. 227-53-003,
Issued: January 29, 1986; Revised: February 13, 1986, whichever is
applicable.
(b) If cracks are found, prior to further flight, contact the
FAA Fort Worth Airplane Certification Office for a reinforcement and
repair scheme provided by Fairchild Aircraft Incorporated and
incorporate this reinforcement and repair scheme.
(c) If no cracks are found, within the next 500 hours after the
initial inspection required in paragraph (a) of this AD, reinforce
the cargo door lower belt frames by installing doublers in
accordance with part B of the Accomplishment Instructions in
Fairchild SB
[[Page 30485]]
226-53-007, Issued: May 7, 1981; Revised: February 17, 1992 or
Fairchild SB 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
compliance times that provides an equivalent level of safety may be
approved by the Manager, FAA, 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 Fort Worth Airplane Certification Office.
(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.
Issued in Kansas City, Missouri, on May 29, 1997.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 97-14544 Filed 6-3-97; 8:45 am]
BILLING CODE 4910-13-U
