[Federal Register Volume 63, Number 73 (Thursday, April 16, 1998)]
[Proposed Rules]
[Pages 18852-18854]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-10055]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-87-AD]
RIN 2120-AA64
Airworthiness Directives; British Aerospace Model BAe 146-200A
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 certain British Aerospace Model
BAe 146-200A series airplanes. This proposal would require a one-time
inspection of the gust damper of the elevator control system to
determine if the gust damper is properly charged, and of the horizontal
stabilizer to detect cracking of elevator hinge rib 1; and corrective
action, if necessary. This proposal is prompted by the 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
[[Page 18853]]
of elevator hinge rib 1 of the horizontal stabilizer, which could occur
if the gust damper of the elevator control system discharges and allows
the elevator to move freely in ground gust conditions. Such cracking
could result in damage to the structural attachment of the elevator to
the horizontal stabilizer, and consequent reduced controllability of
the airplane.
DATES: Comments must be received by May 18, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-87-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 AI(R) American Support, Inc., 13850 Mclearen Road, Herndon,
Virginia 20171. 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-87-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-87-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 certain British Aerospace Model BAe 146-200A
series airplanes. The elevator control system on this model
incorporates a gust damper, which, when properly pressurized with
hydraulic fluid, prevents free movement of the elevators in ground wind
gusts. The CAA advises that two airplanes, which had been stored in the
desert for an extended period of time, were each found to have a
cracked or broken elevator hinge rib 1. Investigation revealed that the
gust damper of the elevator control system on the airplanes was
discharged, which may have been caused by deterioration of the gust
damper seals due to the desert heat. The discharged gust damper of the
elevator control system allowed the elevators on the airplanes to move
freely in ground wind gusts, which resulted in high impact loads on the
elevator hinge rib 1 stops, and consequent cracking of elevator hinge
rib 1 on these airplanes. Such cracking, if not corrected, could result
in damage to the structural attachment of the elevator to the
horizontal stabilizer, and consequent reduced controllability of the
airplane.
Explanation of Relevant Service Information
British Aerospace has issued Service Bulletin SB.55-16, dated July
14, 1997, which describes procedures for performing a one-time visual
inspection of the gust damper of the elevator control system to
determine whether the gust damper is properly charged, and recharging
any gust damper that is found to be improperly charged. This service
bulletin also describes procedures for performing a one-time detailed
visual inspection of the horizontal stabilizer, using a borescope, to
detect cracking of elevator hinge rib 1. Accomplishment of the actions
specified in the service bulletin is intended to adequately address the
identified unsafe condition. The CAA classified this service bulletin
as mandatory and issued British airworthiness directive 010-07-97,
dated March 2, 1998, 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 service bulletin described previously,
except as discussed in the following paragraph.
Differences Between Proposed Rule and Service Bulletin
Operators should note that, although the service bulletin specifies
that the manufacturer should be contacted for repair instructions if
any cracking is found in elevator hinge rib 1, this proposal would
require that discrepant parts be replaced with new or serviceable parts
prior to further flight, in accordance with replacement instructions
provided by the manufacturer and approved by the CAA.
Cost Impact
The FAA estimates that 19 British Aerospace Model BAe 146-200A
series airplanes of U.S. registry would be affected by this proposed
AD. It would take approximately 1 work hour per airplane to accomplish
the proposed inspections, at an average labor rate of $60 per work
hour. Based on these figures, the cost impact of the proposed AD on
U.S. operators is estimated to be $1,140, or $60 per airplane.
[[Page 18854]]
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 Regional Aircraft (Formerly British Aerospace
Regional Aircraft Limited, Avro International Aerospace Division;
British Aerospace, PLC; British Aerospace Commercial Aircraft
Limited): Docket 98-NM-87-AD.
Applicability: Model BAe 146-200A series airplanes, as listed in
British Aerospace Service Bulletin SB.55-16, dated July 14, 1997;
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 detect and correct cracking of elevator hinge rib 1 of the
horizontal stabilizer, which could result in damage to the
structural attachment of the elevator to the horizontal stabilizer
and consequent reduced controllability of the airplane; accomplish
the following:
(a) Within 60 days after the effective date of this AD,
accomplish paragraphs (a)(1) and (a)(2) of this AD, in accordance
with British Aerospace Service Bulletin SB.55-16, dated July 14,
1997.
(1) Perform a visual inspection of the gust damper of the
elevator control system to determine if the gust damper is properly
charged. If any gust damper is found to be improperly charged, prior
to further flight, recharge the gust damper in accordance with the
service bulletin.
(2) Perform a detailed visual inspection, using a borescope, to
detect cracking of elevator hinge rib 1, on the left and right side
of the airplane, in accordance with the service bulletin. If any
cracking is found, prior to further flight, replace any cracked
hinge rib 1 with a new or serviceable part, in accordance with a
method approved by either the Manager, International Branch, ANM-
116, FAA, Transport Airplane Directorate; or procedures provided by
the manufacturer that are approved by the Civil Aviation Authority,
which is the airworthiness authority for the United Kingdom.
(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 010-07-97, dated March 2, 1998.
Issued in Renton, Washington, on April 9, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-10055 Filed 4-15-98; 8:45 am]
BILLING CODE 4910-13-U
