[Federal Register Volume 62, Number 31 (Friday, February 14, 1997)]
[Proposed Rules]
[Pages 6892-6894]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-3696]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-NM-188-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 repetitive
ultrasonic inspections to detect cracking of the lugs of the engine
mounting beams, and replacement of the beam with a serviceable part, if
necessary. This proposal is prompted by reports of fatigue cracking of
the lugs of the engine mounting beams. The actions specified by the
proposed AD are intended to detect and correct such cracking of the
engine mounting lugs, which could result in reduced structural
capability of the engine mount.
DATES: Comments must be received by March 27, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 96-NM-188-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, 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: 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:
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 96-NM-188-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-103, Attention: Rules
Docket No. 96-NM-188-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Civil Aviation Authority (CAA), which is the airworthiness
authority for
[[Page 6893]]
the United Kingdom, recently 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 it has received two reports of fatigue
cracking of the upper rear engine mounting beam. In one instance, the
airplane had accumulated 11,344 flight hours and logged 6,267 landings.
In the other instance, the airplane had accumulated 1,740 flight hours
and logged 858 landings. In the latter instance, the crack of the lug
had opened sufficiently to be detected visually and had propagated in
the longitudinal direction of the beam from the bore to the outside
edge of the lug. Such cracking of the lugs of the engine mounting beam,
if not detected and corrected, could result in reduced structural
capability of the engine mount.
Explanation of Relevant Service Information
British Aerospace has issued Alert Service Bulletin 53-A-PM6032,
Issue 1, dated April 7, 1995, which describes procedures for repetitive
ultrasonic inspections to detect cracking of the lugs of the lower
forward, lower rear, upper forward, and upper rear engine mounting
beams, and replacement of the beam with a serviceable part, if
necessary. The CAA classified this service bulletin as mandatory 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 repetitive
ultrasonic inspections to detect cracking of the lugs of the lower
forward, lower rear, upper forward, and upper rear engine mounting
beams, and replacement of the beam with a serviceable part, if
necessary. The actions would be required to be accomplished in
accordance with the alert service bulletin described previously.
Operators should note that certain compliance times in the proposed
AD are specified in landings or flight hours, as well as calendar time.
The FAA has determined that, since fatigue cracking is directly related
to the number of landings, the compliance times should be specified in
landings that are based on the earliest number of landings known to
have been completed when cracking of the lugs of the engine mounting
beams were detected.
Cost Impact
The FAA estimates that 31 British Aerospace Model BAC 1-11 200 and
400 series airplanes of U.S. registry would be affected by this
proposed AD, that it would take approximately 6 work hours 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 $11,160 or $360 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.
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 96-NM-188-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 (d) 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 of the engine mounting lugs,
which could result in reduced structural capability of the engine
mount; accomplish the following:
(a) Perform an ultrasonic inspection to detect cracking of the
lugs of the lower forward, lower rear, upper forward, and upper rear
of the engine mounting beams in accordance with British Aerospace
Alert Service Bulletin 53-A-PM6032, Issue 1, dated April 7, 1995,
and at the earliest of the times specified in paragraph (a)(1),
(a)(2), or (a)(3) of this AD.
(1) Within 850 landings after the effective date of this AD. Or
(2) Within 1,700 flight hours after the effective date of this
AD. Or
(3) Within 2 years after the effective date of this AD.
(b) If no cracking is detected, repeat the inspection thereafter
at intervals not to
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exceed 1,700 flight hours or 850 landings, whichever occurs first.
(c) If any cracking is detected, prior to further flight,
replace the engine mounting beam in accordance with British
Aerospace Alert Service Bulletin 53-A-PM6032, Issue 1, dated April
7, 1995.
(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
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.
Issued in Renton, Washington, on February 7, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-3696 Filed 2-13-97; 8:45 am]
BILLING CODE 4910-13-U