[Federal Register Volume 64, Number 32 (Thursday, February 18, 1999)]
[Proposed Rules]
[Pages 8027-8029]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-4014]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-307-AD]
RIN 2120-AA64
Airworthiness Directives; British Aerospace Model BAC 1-11 200
and 400 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to all British Aerospace Model BAC 1-
11 200 and 400 series airplanes. This proposal would require an
inspection to detect cracking of the flap control lever and to identify
the material from which the lever is made; replacement of the flap
control lever with an improved part, if necessary; and repetitive
inspections for airplanes having a lever made from certain material.
This proposal is prompted by issuance of mandatory continuing
airworthiness information by a foreign civil airworthiness authority.
The actions specified by the proposed AD are intended to prevent
failure of the flap control lever, which could result in restricted
flap movement and consequent reduced controllability of the airplane.
DATES: Comments must be received by March 22, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-307-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
[[Page 8028]]
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from British Aerospace, Service Support, Airbus Limited, P.O.
Box 77, Bristol BS99 7AR, England. This information may be examined at
the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington.
FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2110; fax (425) 227-1149.
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 shall 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 summarizing 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 Number 98-NM-307-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, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 98-NM-307-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Civil Aviation Authority (CAA), which is the airworthiness
authority for the United Kingdom, notified the FAA that an unsafe
condition may exist on all British Aerospace Model BAC 1-11 200 and 400
series airplanes. The CAA has received two reports of cracking of flap
control levers installed on these airplanes. Certain control levers
were cast from L53 aluminum alloy, a material which is known to be
prone to stress corrosion cracking. Such stress corrosion cracking
could cause failure of the flap control lever. This condition, if not
corrected, could result in restricted flap movement and consequent
reduced controllability of the airplane.
Explanation of Relevant Service Information
British Aerospace has issued Alert Service Bulletin 27-A-PM6041,
Issue 1, dated August 21, 1998, which describes procedures for a one-
time detailed visual inspection to detect cracking of the flap control
lever and to identify the material from which the lever is made;
replacement of the flap control lever with an improved part, if
necessary; and repetitive inspections for airplanes having a lever made
from certain material. Accomplishment of the actions specified in the
alert service bulletin is intended to adequately address the identified
unsafe condition. The CAA classified this alert service bulletin as
mandatory and issued British airworthiness directive 003-08-98 in order
to assure the continued airworthiness of these airplanes in the United
Kingdom.
FAA's Conclusions
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
21.29) 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, and determined
that AD action is necessary for products of this type design that are
certificated for operation in the United States.
Explanation of Requirements of Proposed Rule
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, the proposed AD would require accomplishment of
the actions specified in the alert service bulletin described
previously.
Cost Impact
The FAA estimates that 42 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 1 work
hour per airplane to accomplish the proposed actions, and that the
average labor rate is $60 per work hour. Based on these figures, the
cost impact of the proposed AD on U.S. operators is estimated to be
$2,520, or $60 per airplane.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed requirements of
this AD action, and that no operator would accomplish those actions in
the future if this AD were not adopted.
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 proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the 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 is contained 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.
[[Page 8029]]
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
British Aerospace Airbus Limited (Formerly British Aerospace
Commercial Aircraft Limited, British Aerospace Aircraft Group):
Docket 98-NM-307-AD.
Applicability: All Model BAC 1-11 200 and 400 series airplanes;
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 (b) 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, unless accomplished
previously.
To prevent failure of the flap control lever, which could result
in restricted flap movement and consequent reduced controllability
of the airplane, accomplish the following:
(a) Within 12 months after the effective date of this AD,
perform a one-time detailed visual inspection of the flap control
lever to detect cracking, and to identify the type of aluminum alloy
from which the flap control lever is made, in accordance with
British Aerospace Alert Service Bulletin 27-A-PM6041, Issue 1, dated
August 21, 1998.
(1) If no crack is detected and the lever is made of L97 or L99
aluminum alloy, no further action is required by this AD.
(2) If no crack is detected, and the lever is made of L53
aluminum alloy or the material of the flap control lever cannot be
identified, repeat the inspection thereafter at intervals not to
exceed 24 months; or prior to further flight, replace the flap
control lever with a flap control lever made of L97 or L99 aluminum
alloy, in accordance with the alert service bulletin. Following such
replacement, no further action is required by this AD.
(3) If any crack is detected, prior to further flight, replace
the flap control lever with a flap control lever made of L97 or L99
aluminum alloy, in accordance with the alert service bulletin. After
the replacement, no further action is required by this AD.
(b) 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, International Branch, ANM-116, 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, International
Branch, ANM-116
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(c) 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.
Note 3: The subject of this AD is addressed in British
airworthiness directive 003-08-98.
Issued in Renton, Washington, on February 11, 1999.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-4014 Filed 2-17-99; 8:45 am]
BILLING CODE 4910-13-U
