[Federal Register Volume 63, Number 76 (Tuesday, April 21, 1998)]
[Proposed Rules]
[Pages 19682-19684]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-10475]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-51-AD]
RIN 2120-AA64
Airworthiness Directives; British Aerospace 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 repetitive
detailed visual inspections to detect cracking in the trunnion fittings
located in the nose landing gear (NLG) bay of the forward fuselage; and
repair, if necessary. 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 detect and correct cracking in the trunnion fittings of the
NLG, which could lead to collapse of the NLG during takeoff and
landing, and possible injury to the flight crew and passengers.
DATES: Comments must be received by May 21, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-51-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056. Comments may be inspected at this 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:
[[Page 19683]]
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-51-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-51-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 advises that operators have reported cracks
in the trunnion fittings located in the nose landing gear (NLG) bay on
the forward fuselage. The cracks propagated through the material
thickness in the area of the trunnion cap attachment holes, on both the
left- and right-hand trunnion fittings. Laboratory examination
indicates that the damage to the trunnion fittings is characteristic of
stress corrosion cracking. Additionally, service experience has
indicated that certain BAC 1-11 200 and 400 series airplanes on which
British Aerospace Modification 5308 has been accomplished may be more
prone to such cracking and, therefore, a more stringent inspection
schedule is required for these airplanes. (British Aerospace
Modification 5308 introduces new bearing assemblies and trunnion caps,
and strengthening of associated components.) Such cracking in the
trunnion fittings, if not detected and corrected, could lead to
collapse of the NLG during takeoff and landing, and possible injury to
the flight crew and passengers.
Explanation of Relevant Service Information
British Aerospace has issued Alert Service Bulletin 53-A-PM6035,
Revision 1, dated March 7, 1996, which describes procedures for
repetitive detailed visual inspections to detect cracking on the left-
and right-hand trunnion fittings of the NLG in the area of the trunnion
cap attachment holes on both the inner and outer faces of the fitting.
The CAA classified this alert service bulletin as mandatory and issued
British airworthiness directive 004-03-96, dated April 26, 1996, 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 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, 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. The actions would be required to be accomplished in
accordance with the alert service bulletin described previously, except
as discussed below.
Differences Between Proposed Rule and Service Bulletin
Operators should note that, although the alert service bulletin
specifies that the manufacturer may be contacted for repairing crack
conditions, this proposal would require the repair of those conditions
to be accomplished in accordance with a method approved by the FAA.
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 inspection, 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:
[[Page 19684]]
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 the following new
airworthiness directive:
British Aerospace Airbus Limited (Formerly British Aerospace
Commercial Aircraft Limited, British Aerospace Aircraft Group):
Docket 98-NM-51-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 (c) 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 detect and correct cracking in the trunnion fittings of the
nose landing gear (NLG), which could lead to collapse of the NLG
during takeoff and landing, and possible injury to the flight crew
and passengers, accomplish the following:
(a) Perform a detailed visual inspection for cracking on the
left- and right-hand trunnion fittings of the NLG, in the area of
the trunnion cap attachment holes, in accordance with British
Aerospace Alert Service Bulletin 53-A-PM6035, Revision 1, dated
March 7, 1996; at the time specified in paragraph (a)(1) or (a)(2)
of this AD, as applicable.
(1) For airplanes on which British Aerospace Modification PM5308
has not been accomplished: Perform the inspection within 6 years
after the effective date of this AD, or within 11 years after the
last inspection accomplished in accordance with the alert service
bulletin, whichever occurs later. Repeat the inspection thereafter
at intervals not to exceed 11 years.
(2) For airplanes on which British Aerospace Modification PM5308
has been accomplished: Perform the inspection within 30 months after
the effective date of this AD, or within 5 years after the last
inspection accomplished in accordance with the alert service
bulletin, whichever occurs later. Repeat the inspection thereafter
at intervals not to exceed 6 years.
(b) If any crack is found during any inspection required by
paragraph (a) of this AD, prior to further flight, repair the crack
in accordance with a method approved by the Manager, International
Branch, ANM-116, FAA, Transport Airplane Directorate.
(c) 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.
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.
(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.
Note 3: The subject of this AD is addressed in the British
airworthiness directive 004-03-96, dated April 26, 1996.
Issued in Renton, Washington, on April 15, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-10475 Filed 4-20-98; 8:45 am]
BILLING CODE 4910-13-U
