[Federal Register Volume 60, Number 80 (Wednesday, April 26, 1995)]
[Proposed Rules]
[Pages 20461-20463]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-10202]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-161-D]
Airworthiness Directives; British Aerospace BAC 1-11-200 and -400
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to all British Aerospace BAC 1-11-200
and -400 series airplanes. This proposal would require repetitive
radiographic inspections to detect corrosion of the center torque shaft
of the wing spoiler, and replacement, if necessary. This proposal is
prompted by a report of the wing spoiler failing to retract fully after
deployment, which caused the wing to drop significantly. Subsequent
investigation revealed that the torque shaft assembly of the wing
spoiler had failed, due to severe corrosion. The actions specified by
the proposed AD are intended to prevent such failures, which can result
in an adverse effect on controllability of the airplane.
DATES: Comments must be received by May 5, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-161-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: William Schroeder, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2148; fax (206) 227-1320.
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 94-NM-161-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. 94-NM-161-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
[[Page 20462]]
Discussion
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 all British Aerospace Model BAC 1-11-200
and -400 series airplanes. The CAA advises that it has received a
report of a failure of a wing spoiler on one airplane to retract fully
after deployment. This failure caused the airplane wing to drop
significantly. Subsequent investigation revealed that the center torque
shaft of the wing spoiler had failed due to severe corrosion present on
the internal surface of the shaft assembly. Such corrosion, if not
detected and corrected in a timely manner, could cause the torque shaft
to fail and, consequently, cause the airplane wing to drop
significantly; this would result in an adverse effect on
controllability of the airplane.
British Aerospace has issued Alert Service Bulletin 27-A-PM6007,
Issue 1, dated April 10, 1992, which describes procedures for
accomplishing repetitive radiographic inspections for corrosion of the
center torque shaft of the spoiler on the left and right wing, and
replacement of the shaft assembly, if necessary. 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 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.
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
repetitive radiographic inspections to detect corrosion of the center
torque shaft of the wing spoiler, and replacement of the torque shaft
assembly, if necessary. The actions would be required to be
accomplished in accordance with the service bulletin described
previously.
As a result of recent communications with the Air Transport
Association (ATA) of America, the FAA has learned that, in general,
some operators may misunderstand the legal effect of AD's on airplanes
that are identified in the applicability provision of the AD, but that
have been altered or repaired in the area addressed by the AD. The FAA
points out that all airplanes identified in the applicability provision
of an AD are legally subject to the AD. If an airplane has been altered
or repaired in the affected area in such a way as to affect compliance
with the AD, the owner or operator is required to obtain FAA approval
for an alternative method of compliance with the AD, in accordance with
the paragraph of each AD that provides for such approvals. A note has
been included in this notice to clarify this requirement.
The FAA estimates that 31 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 40 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
total cost impact of the proposed AD on U.S. operators is estimated to
be $74,400, or $2,400 per airplane, per inspection cycle.
Should an operator be required to accomplish the replacement of the
torque shaft assembly, it would take approximately 40 work hours per
airplane to accomplish, at an average labor rate of $60 per work hour.
Required parts will cost approximately $2,950 per airplane. Based on
these figures, the total cost impact of any necessary replacement
action is estimated to be $5,350 per airplane.
The total 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.
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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
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 94-NM-161-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 use the authority
provided in paragraph (d) 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 failure of the center torque shaft of the spoiler on
the left and right wing, accomplish the following:
(a) Perform a radiographic inspection to detect internal
corrosion of the center torque shaft on the left and right wing
spoilers, in accordance with the Accomplishment Instructions of
British Aerospace BAC 1-11 [[Page 20463]] Alert Service Bulletin 27-
A-PM6007, Issue 1, dated April 10, 1992, at the time specified in
paragraph (a)(1) or (a)(2) of this AD, as applicable. If the date of
installation of a center torque shaft cannot be determined, the
radiographic inspection of that shaft must be accomplished within 9
months after the effective date of this AD.
(1) For the center torque shaft on the left wing spoiler:
Inspect within 10 years after the date of installation of that
center torque shaft, or within 9 months after the effective date of
this AD, whichever occurs later.
(2) For the center torque shaft on the right wing spoiler:
Inspect within 10 years after the date of installation of that
center torque shaft, or within 9 months after the effective date of
this AD, whichever occurs later.
(b) If no internal corrosion is detected, repeat the
radiographic inspection required by paragraph (a) of this AD
thereafter at intervals not to exceed 4 years.
(c) If any internal surface corrosion is detected, prior to
further flight, replace that shaft assembly with either a used
serviceable assembly or a new assembly, in accordance with British
Aerospace Alert Service Bulletin 27-A-PM6007, Issue 1, dated April
10, 1992. Perform the radiographic inspection in accordance with
that service bulletin at the applicable time specified in paragraph
(c)(1) or (c)(2) of this AD.
(1) If a new shaft assembly is installed: Perform the inspection
within 10 years after installation. Thereafter, repeat the
inspection at intervals not to exceed 4 years.
(2) If a used serviceable shaft is installed: Prior to
installation, perform an initial radiographic inspection of that
shaft in accordance with the service bulletin. Thereafter, repeat
the inspection at intervals not to exceed 4 years.
(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.
Issued in Renton, Washington, on April 20, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-10202 Filed 4-25-95; 8:45 am]
BILLING CODE 4910-13-U