[Federal Register Volume 60, Number 221 (Thursday, November 16, 1995)]
[Rules and Regulations]
[Pages 57540-57542]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-27912]
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[[Page 57541]]
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-210-AD; Amendment 39-9428; AD 95-23-08]
Airworthiness Directives; Avro Model BAe 146 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Avro Model BAe 146 series airplanes. This action
requires inspections to detect cracking and damage of the fastener
holes in the butt strap at rib 2 at the lower surface of the right-hand
wing; repair of discrepancies; and replacement of the fastener bolts.
This amendment is prompted by a report that certain wings were
manufactured with a reduction in the amount of edge margin between the
fastener hole centers and the edge of the butt strap; this condition
can result in a decrease in the long-term damage tolerance residual
strength of the wing. The actions specified in this AD are intended to
prevent cracking and other problems associated with a such decrease in
the long-term damage tolerance residual strength of the wing.
DATES: Effective December 1, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 1, 1995.
Comments for inclusion in the Rules Docket must be received on or
before January 16, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-210-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
The service information referenced in this AD may be obtained from
British Aerospace Holdings, Inc., Avro International Aerospace
Division, P.O. Box 16039, Dulles International Airport, Washington, DC
20041-6039. This information may be examined at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2797; fax (206) 227-1149.
SUPPLEMENTARY INFORMATION: The Civil Aviation Authority (CAA), which is
the airworthiness authority for the United Kingdom, recently notified
the FAA that an unsafe condition may exist on certain Avro Model BAe
146 series airplanes. The CAA advises that four wing-sets, delivered
from the vendor and installed on four airplanes, were manufactured with
a marked reduction in the amount of edge margin between the fastener
hole centers and edge of the rib 2 butt strap on the lower surface of
the right-hand wing. (Edge margin is defined as the distance from the
center of the fastener hole to the nearest edge of the part.) A
reduction in edge margin could lead to a decrease in the long-term
damage tolerance residual strength of the wing. This condition, if not
corrected, could result in fatigue cracking and other damage occurring
in the subject area at a time that is earlier than anticipated.
Avro International Aerospace has issued Service Bulletin 57-40,
dated March 18, 1994. This service bulletin describes procedures for
removing four specific fasteners from the rib 2 butt strap on the lower
surface of the right-hand wing, and conducting an eddy current
inspection to detect cracking of the vacant fastener holes. The service
bulletin also describes procedures for conducting a visual inspection
of the fastener holes to detect other damage, such as scoring that has
resulted from removal of the bolts; and to check the diameter of each
hole to determine if it is within the allowable tolerance. The service
bulletin also contains procedures for repairing cracked, damaged, or
incorrectly sized holes by oversizing them, and for installing new
fastener bolts. The CAA classified this service bulletin as mandatory
in order to assure the continued airworthiness of these airplanes in
the United Kingdom.
This airplane model is manufactured in the United Kingdom and is
type certificated for operation in the United States under the
provisions of section 21.29 of the Federal Aviation Regulations (14 CFR
21.19) and the applicable bilateral airworthiness agreement. Pursuant
to this bilateral airworthiness agreement, the CAA has kept the FAA
informed of the situation described above. The FAA has examined the
findings of the CAA, reviewed all available information, and determined
that AD action is necessary for products of this type design that are
certificated for operation in the United States.
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, this AD is being issued to prevent cracking and
other problems associated with a decrease in the long-term damage
tolerance residual strength of the wing. This AD requires repetitive
eddy current inspections to detect cracking of the 4 fastener holes at
the rib 2 butt strap on the lower surface of the right-hand wing. It
also requires repetitive visual inspections of the fastener holes to
detect other damage, such as scoring that has resulted from removal of
the bolts; and to check the diameter of each fastener hole to determine
if it is within the allowable tolerance. If no cracking or damage is
detected in a fastener hole, and if the hole's diameter is within
tolerance limits, a new bolt must be installed. If any cracking or
damage is detected, or if the hole's diameter is outside of tolerance
limits, the hole must be oversized and cleaned, and a new bolt must be
installed. The actions are required to be accomplished in accordance
with the service bulletin described previously.
None of the Model BAe 146 series airplanes affected by this action
are on the U.S. Register. All airplanes included in the applicability
of this rule currently are operated by non-U.S. operators under foreign
registry; therefore, they are not directly affected by this AD action.
However, the FAA considers that this rule is necessary to ensure that
the unsafe condition is addressed in the event that any of these
subject airplanes are imported and placed on the U.S. Register in the
future.
Should an affected airplane be imported and placed on the U.S.
Register in the future, it would require approximately 8 work hours to
accomplish the required actions, at an average labor charge of $60 per
work hour. Based on these figures, the total cost impact of this AD
would be $480 per airplane.
Since this AD action does not affect any airplane that is currently
on the U.S. register, it has no adverse economic impact and imposes no
additional burden on any person. Therefore, notice and public
procedures hereon are unnecessary and the amendment may be made
effective in less than 30 days after publication in the Federal
Register.
Comments Invited
Although this action is in the form of a final rule and was not
preceded by notice and opportunity for public comment, comments are
invited on this rule. Interested persons are invited to comment on this
rule by submitting such written data, views, or arguments as they may
desire. Communications shall identify the Rules Docket number
[[Page 57542]]
and be submitted in triplicate to the address specified under the
caption ADDRESSES. All communications received on or before the closing
date for comments will be considered, and this rule may be amended in
light of the comments received. Factual information that supports the
commenter's ideas and suggestions is extremely helpful in evaluating
the effectiveness of the AD action and determining whether additional
rulemaking action would be needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 95-NM-210-AD.'' The postcard will be date stamped and
returned to the commenter.
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 final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from 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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-23-08 Avro International Aerospace (Formerly British Aerospace):
Amendment 39-9428. Docket 95-NM-210-AD.
Applicability: Model BAe 146 series airplanes; having
constructors' numbers E2188, E2192, E3190, and E3194; certificated
in any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
otherwise 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 (d) 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 as indicated, unless accomplished
previously.
To prevent cracking and other problems associated with a
decrease in the long-term damage tolerance residual strength of the
wing, accomplish the following:
(a) Prior to the accumulation of 36,000 total landings or within
3 months after the effective date of this AD, whichever occurs
later, remove the 4 fasteners from the rib 2 butt strap on the lower
wing surface of the right-hand wing and accomplish the requirements
of paragraphs (a)(1) and (a)(2) of this AD, in accordance with Avro
Service Bulletin 57-40, dated March 19, 1994: -
(1) Perform an eddy current inspection of each of the fastener
holes to detect cracking.
(2) Perform a visual inspection of each of the fastener holes to
detect evidence of damage, such as scoring that has resulted from
removal of the bolts; and to check the diameter of each hole to
determine if it is within the allowable tolerance specified in the
service bulletin.
(b) If the fastener hole is free of cracks and damage, and if
the hole's diameter is within the allowable tolerance, prior to
further flight, install a new bolt in accordance with the service
bulletin. Thereafter, repeat the inspections specified in paragraph
(a) of this AD at intervals not to exceed 9,000 landings.
(c) If the hole is cracked or shows evidence of damage, or if
the hole's diameter is outside the allowable tolerance, prior to
further flight, oversize the hole, clean out the damage, and install
a new bolt, in accordance with the service bulletin. Thereafter,
repeat the inspections specified in paragraph (a) of this AD at
intervals not to exceed 9,000 landings.
(d) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, Standardization Branch, ANM-113,
FAA, Transport Airplane Directorate. Operators shall submit their
requests through an appropriate FAA Principal Maintenance Inspector,
who may add comments and then send it to the Manager,
Standardization Branch, ANM-113.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(e) 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.
(f) The actions shall be done in accordance with Avro Service
Bulletin 57-40, dated March 18, 1994. 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 British Aerospace Holdings, Inc., Avro International
Aerospace Division, P.O. Box 16039, Dulles International Airport,
Washington, DC 20041-6039. Copies may be inspected at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the Office of the Federal Register, 800 North
Capitol Street, NW., suite 700, Washington, DC.
(g) This amendment becomes effective on December 1, 1995.
Issued in Renton, Washington, on November 6, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-27912 Filed 11-15-95; 8:45 am]
BILLING CODE 4910-13-U
