[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