[Federal Register Volume 60, Number 201 (Wednesday, October 18, 1995)]
[Rules and Regulations]
[Pages 53853-53855]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-25450]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-189-AD; Amendment 39-9400; AD 95-21-13]
Airworthiness Directives; British Aerospace Model BAe 146 and
Model Avro 146-RJ Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to all British Aerospace Model BAe 146 and Model Avro
146-RJ series airplanes. This action requires inspection(s) to detect
damaged and missing surface protective finish, corrosion, and cracking
on the servo tab brackets and the trim tab drive brackets of the
aileron, and corrective actions, if necessary. This amendment is
prompted by a report of corrosion on an aileron tab bracket between the
two tab drive flanges in the area of the two attachment bolts, which
resulted in cracking of the flanges at their base. The actions
specified in this AD are intended to prevent the failure of the servo
tab brackets and trim tab drive brackets of the aileron due to cracking
associated with corrosion, which could result in reduced
controllability of the airplane.
DATES: Effective November 2, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 2, 1995.
Comments for inclusion in the Rules Docket must be received on or
before December 18, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-189-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
The service information referenced in this AD may be obtained from
British Aerospace Holding, Inc., Avro International Aerospace Division,
P.O. Box 16039, Dulles International Airport, Washington DC 20041-6039.
This information may be examined at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
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) 227-1149.
SUPPLEMENTARY INFORMATION: 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 BAe 146 and Model Avro 146-RJ series airplanes. The CAA advises
that it has received a
[[Page 53854]]
report of corrosion on an aileron tab bracket between the two tab drive
flanges in the area of the two attachment bolts. Such corrosion
resulted in cracking of the bracket flanges at their base. The effects
of such corrosion and resultant cracking could lead to the failure of
the servo tab brackets and the trim tab drive brackets of the aileron.
This condition, if not corrected, could result in reduced
controllability of the airplane.
British Aerospace has issued Service Bulletin S.B. 57-47, dated
June 15, 1995 (for Model BAe 146 series airplanes), and Service
Bulletin S.B. 57-48, dated June 30, 1995 (for Model Avro 146-RJ series
airplanes). These service bulletins describe procedures for detailed
visual inspection(s) to detect damaged and missing surface protective
finish, corrosion, and cracking on the servo tab brackets and the trim
tab drive brackets of the aileron, and corrective actions, if
necessary. These service bulletins also describe procedures for
replacement of any cracked servo tab bracket or trim tab bracket with a
new bracket. The CAA classified these service bulletins 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 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.
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, this AD is being issued to prevent the failure of
the servo tab brackets and the trim tab drive brackets of the aileron
due to cracking associated with corrosion, which could result in
reduced controllability of the airplane. This AD requires detailed
visual inspection(s) to detect damaged and missing surface protective
finish, corrosion, and cracking on the servo tab brackets and the trim
tab drive brackets (a total of six brackets) of the aileron, and
corrective actions, if necessary. This AD also requires replacement of
any cracked servo tab bracket or trim tab bracket with a new bracket.
The actions are required to be accomplished in accordance with the
service bulletins described previously.
The FAA is considering further rulemaking action to supersede this
AD to require, for certain airplanes, removal of the servo tab bracket
and trim tab drive bracket of the aileron, a detailed visual inspection
to detect damaged or missing surface protective finish, corrosion, or
cracking, and corrective actions. However, the planned compliance time
for these actions is sufficiently long so that notice and time for
public comment would not be impracticable.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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 that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 95-NM-189-AD.'' The postcard will be date stamped and
returned to the commenter.
The regulations adopted herein will 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 final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, may be obtained from the Rules Docket at the
location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends 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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-21-13 British Aerospace Regional Aircraft Limited, Avro
International Aerospace Division (Formerly British Aerospace, plc;
British Aerospace Commercial Aircraft Limited): Amendment 39-9400.
Docket 95-NM-189-AD.
Applicability: All Model BAe 146 series airplanes; and all Model
Avro 146-RJ series airplanes, all line numbers up to and
[[Page 53855]]
including line number E3263; 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 (c) of this AD 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 the failure of the servo and trim tab drive brackets
of the aileron due to cracking associated with corrosion, which
could result in reduced controllability of the airplane, accomplish
the following:
(a) Within 14 days after the effective date of this AD, perform
a detailed visual inspection to detect damaged or missing surface
protective finish, corrosion, or cracking on the servo tab brackets
and the trim tab drive brackets of the aileron (total of 6
brackets), in accordance with British Aerospace Service Bulletin
S.B. 57-47, dated June 15, 1995 (for Model BAe 146 series
airplanes), or British Aerospace Service Bulletin S.B. 57-48, dated
June 30, 1995 (for Model Avro 146-RJ series airplanes), as
applicable.
(1) If no discrepancy is found, no further action is required by
this AD.
(2) If any discrepancy is found on the surface protection
finish, but no corrosion or cracking is detected on any servo tab
bracket or trim tab drive bracket, prior to further flight, reapply
the intermediate (barrier) coat and the strippable polyurethane
gloss top coat (aluminum colored), in accordance with the applicable
service bulletin.
(3) If any corrosion, but no cracking, is detected on the servo
tab bracket or trim tab drive bracket, repeat the inspection
thereafter at intervals not to exceed 50 landings. Prior to the
accumulation of 500 landings after the initial inspection, remove
corrosion and reapply the intermediate (barrier) coat and the
strippable polyurethane gloss top coat (aluminum colored), in
accordance with the applicable service bulletin.
(4) If any cracking is detected on the servo tab drive bracket,
prior to further flight, replace the cracked bracket with a new
bracket, in accordance with the applicable service bulletin. After
accomplishing the replacement, no further action is required by this
AD for that servo tab bracket.
(5) If any cracking is detected in only one flange of a single
trim tab drive bracket and no other discrepancy is detected, repeat
the inspection thereafter at intervals not to exceed 10 landings.
Prior to the accumulation of 50 landings after the initial
inspection, replace the cracked trim tab drive bracket with a new
bracket, in accordance with the applicable service bulletin. After
accomplishing the replacement, no further action is required by this
AD for that trim tab drive bracket.
(6) If any cracking is detected in the trim tab drive bracket
and the crack has propagated through the flange or cracking exists
in more than one flange of the bracket, prior to further flight,
replace the cracked trim tab drive bracket with a new bracket, in
accordance with the applicable service bulletin. After accomplishing
the replacement, no further action is required by this AD for that
trim tab drive bracket.
(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, 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.
(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.
(d) The actions shall be done in accordance with British
Aerospace Service Bulletin S.B. 57-47, dated June 15, 1995, or
British Aerospace Service Bulletin S.B. 57-48, dated June 30, 1995,
as applicable. This incorporation by reference was approved by the
Director of the Federal Register in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. Copies may be obtained from British Aerospace
Holding, Inc., Avro International Aerospace Division, P.O. Box
16039, Dulles International Airport, Washington DC 20041-6039.
Copies may be inspected at the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
(e) This amendment becomes effective on November 2, 1995.
Issued in Renton, Washington, on October 6, 1995.
Gary L. Killion,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-25450 Filed 10-17-95; 8:45 am]
BILLING CODE 4910-13-U
