[Federal Register Volume 63, Number 50 (Monday, March 16, 1998)]
[Proposed Rules]
[Pages 12708-12710]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-6592]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-CE-03-AD]
RIN 2120-AA64
Airworthiness Directives; British Aerospace (Operations) Limited
Model B.121 Series 1, 2, and 3 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 British Aerospace (Operations) Limited
(British Aerospace) Model B.121 Series 1, 2, and 3 airplanes. The
proposed AD would require installing an inspection opening in the area
of the main spar web, repetitively inspecting the area at the main spar
web for cracks and the area of the wing to fuselage attach bolt holes
for corrosion, and repairing or replacing any cracked or corroded part.
The
[[Page 12709]]
proposed AD is the result of mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for the United
Kingdom. The actions specified by the proposed AD are intended to
prevent structural failure of the main spar web area caused by fatigue
cracking or separation of the wing from the fuselage caused by corroded
attach bolt holes, which could result in loss of control of the
airplane.
DATES: Comments must be received on or before April 17, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 98-CE-03-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 British Aerospace (Operations) Limited, British Aerospace Regional
Aircraft, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland;
telephone: (01292) 479888; facsimile: (01292) 479703. This information
also may be examined at the Rules Docket at the address above.
FOR FURTHER INFORMATION CONTACT: Mr. Roger Chudy, Aerospace Engineer,
Small Airplane Directorate, Aircraft Certification Service, 1201
Walnut, suite 900, Kansas City, Missouri 64106; telephone: (816) 426-
6932; facsimile: (816) 426-2169.
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. 98-CE-03-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 Regional Counsel, Attention:
Rules Docket No. 98-CE-03-AD, Room 1558, 601 E. 12th Street, Kansas
City, Missouri 64106.
Discussion
The Civil Airworthiness Authority (CAA), which is the airworthiness
authority for the United Kingdom, recently notified the FAA that an
unsafe condition may exist on certain British Aerospace Model B.121
Series 1, 2, and 3 airplanes. The CAA reports findings of fatigue
cracking in the area of the main-spar next to the undercarriage attach
points, and corrosion at the wing/spar attach bolt holes.
These conditions, if not corrected in a timely manner, could result
in structural failure of the main spar web area caused by fatigue
cracking or separation of the wing from the fuselage caused by corroded
attach bolt holes, with consequent loss of control of the airplane.
Relevant Service Information
British Aerospace has issued PUP Service Bulletin No. B121/102,
Revision No. 1, Issued April 16, 1997, which specifies procedures for
the following:
--Installing an inspection opening and inspecting, using eddy current
methods, the area at the main spar web for cracks; and
--Visually inspecting the area of the wing to fuselage attach bolt
holes for corrosion.
The CAA classified this service bulletin as mandatory and issued
British AD 005-10-96, not dated, in order to assure the continued
airworthiness of these airplanes in the United Kingdom.
The FAA's Determination
This airplane model is manufactured in the United Kingdom and is
type certificated for operation in the United States under the
provisions of Sec. 21.29 of the Federal Aviation Regulations (14 CFR
21.29) 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, including the service information referenced
above; and determined that AD action is necessary for products of this
type design that are certificated for operation in the United States.
Explanation of the Provisions of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop in other British Aerospace Model B.121 Series 1, 2,
and 3 airplanes of the same type design registered in the United
States, the FAA is proposing AD action. The proposed AD would require
installing an inspection opening in the area of the main spar web,
repetitively inspecting the area at the main spar web for cracks and
the area of the wing to fuselage attach bolt holes for corrosion, and
repairing or replacing any cracked or corroded part. Accomplishment of
the proposed inspections would be required in accordance with British
Aerospace PUP Service Bulletin No. B121/102, Revision No. 1, Issued
April 16, 1997. If necessary, the proposed repair or replacement would
be required in accordance with a scheme obtained from the manufacturer
through the FAA, Small Airplane Directorate.
Cost Impact
The FAA estimates that 2 airplanes in the U.S. registry would be
affected by the proposed AD, that it would take approximately 18
workhours per airplane to accomplish the proposed initial inspection
and inspection opening installation, and that the average labor rate is
approximately $60 an hour. Based on these figures, the total cost
impact of the proposed AD on U.S. operators is estimated to be $2,160,
or $1,080 per airplane. These figures only take into account the cost
of the proposed initial inspections and inspection opening
installation, and do not take into account the cost of repetitive
inspections. The FAA has no way of determining the number of repetitive
inspections each owner/operator of the affected airplanes will incur.
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
[[Page 12710]]
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. 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:
British Aerospace (Operations) Limited: Docket No. 98-CE-03-AD.
Applicability: Model B.121 Series 1, 2, and 3 airplanes, all
serial numbers, certificated in any category.
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 in the body of this AD, unless
already accomplished.
To prevent structural failure of the main spar web area caused
by fatigue cracking or separation of the wing from the fuselage
caused by corroded attach bolt holes, which could result in loss of
control of the airplane, accomplish the following:
(a) Within the next 100 hours time-in-service (TIS) after the
effective date of this AD, accomplish the following in accordance
with the Accomplishment Instructions section, Appendix 1, and
Appendix 2 of British Aerospace PUP Service Bulletin No. B121/102,
Revision No. 1, dated April 16, 1997:
(1) Install an inspection opening and inspect, using eddy
current methods, the area at the main spar web for cracks; and
(2) Visually inspect the area of the wing to fuselage attach
bolt holes for corrosion.
(b) Within 800 hours TIS after the initial inspection required
by paragraph (a), including subparagraphs, of this AD, and
thereafter at intervals not to exceed 800 hours TIS, reinspect the
area of the main spar web as specified in paragraph (a), including
all subparagraphs, of this AD.
(c) If any cracks or corrosion damage is found during any
inspection required by this AD, prior to further flight, accomplish
the following:
(1) Obtain a repair or replacement scheme from the manufacturer
through the FAA, Small Airplane Directorate, at the address
specified in paragraph (e) of this AD; and
(2) Incorporate this scheme and continue to repetitively inspect
as required by paragraph (b) of this AD, unless specified
differently in the instructions to the repair or replacement scheme.
(d) 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.
(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, Small Airplane
Directorate, Aircraft Certification Service, 1201 Walnut, suite 900,
Kansas City, Missouri 64106. The request shall be forwarded through
an appropriate FAA Maintenance Inspector, who may add comments and
then send it to the Manager, Small Airplane Directorate.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Small Airplane Directorate.
(f) Questions or technical information related to British
Aerospace PUP Service Bulletin No. B121/102, Revision No. 1, Issued
April 16, 1997, should be directed to British Aerospace (Operations)
Limited, British Aerospace Regional Aircraft, Prestwick
International Airport, Ayrshire, KA9 2RW, Scotland; telephone:
(01292) 479888; facsimile: (01292) 479703. This service information
may be examined at the FAA, Central Region, Office of the Regional
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.
Note 3: The subject of this AD is addressed in British AD 005-
10-96, not dated.
Issued in Kansas City, Missouri, on March 9, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-6592 Filed 3-13-98; 8:45 am]
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