[Federal Register Volume 61, Number 153 (Wednesday, August 7, 1996)]
[Proposed Rules]
[Pages 41037-41039]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-20073]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-213-AD]
RIN 2120-AA64
Airworthiness Directives; British Aerospace Model Avro 146-RJ70A,
-RJ85A, and -RJ100A 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
Avro 146-RJ70A, -RJ85A, and -RJ100A airplanes. This proposal would
require repetitive inspections for cracking of fuselage frame 29, and
repair, if necessary. This proposal is prompted by results of fatigue
testing, which revealed fatigue cracking in the web and inboard flange
of frame 29. The actions specified by the proposed AD are intended to
prevent reduced structural integrity of the fuselage due to fatigue
cracking in frame 29.
DATES: Comments must be received by September 16, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-213-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 Regional Aircraft Limited, Avro
International Aerospace Division, Customer Support, Woodford Aerodrome,
Woodford, Cheshire SK7 1QR, 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 95-NM-213-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. 95-NM-213-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
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 certain British Aerospace Model Avro 146-
RJ70A,-RJ85A, and-RJ100A airplanes. The CAA advises that, during
fatigue testing of the fuselage, cracking was discovered in the web and
inboard flange of frame 29 between stringers 12 and 18 on the left and
right side of the fuselage. The cracking emanated from the bolt holes
in these areas. Such fatigue cracking, if not detected and corrected in
a timely manner, could result in reduced structural integrity of the
fuselage of the airplane.
Explanation of Relevant Service Information
The manufacturer has issued Avro International Aerospace Inspection
Service Bulletin S.B. 53-131, dated March 29, 1995, which describes
procedures for repetitive visual inspections of frame 29 between
stringers 12 and 18 on the left and right side of the fuselage. The
service bulletin also references procedures for accomplishing a
modification at each affected bolt position, which would eliminate the
need for the repetitive inspections when the modification is installed
at the time specified in the service bulletin. (Specific procedures for
this modification are described in Repair Instruction Leaflet
HC536H9168.) 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
These airplane models are manufactured in the United Kingdom and
are 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
[[Page 41038]]
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, the
proposed AD would require repetitive visual inspections to detect
cracking of the fuselage at frame 29. The actions would be required to
be accomplished in accordance with the service bulletin described
previously. All findings of cracking would be required to be repaired
in accordance with a method approved by the FAA.
Additionally, the proposed AD would provide for an optional
terminating action for the repetitive inspections. Terminating action
would consist of modifying each affected bolt position in accordance
with the service bulletin described previously, provided that the
modification is accomplished no later than the applicable time
specified in that service bulletin.
Cost Impact
The FAA estimates that 11 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 9 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
$5,940, or $540 per airplane, per inspection cycle.
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: Docket 95-NM-213-AD.
Applicability: Model Avro 146-RJ70A, -RJ85A, and -RJ100A
airplanes; as listed in Avro International Aerospace Inspection
Service Bulletin S.B. 53-131, dated March 29, 1995; certificated in
any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
otherwise 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 prevent reduced structural integrity of the fuselage of the
airplane due to fatigue cracking in frame 29, accomplish the
following:
(a) Perform a detailed visual inspection for cracking of frame
29 between stringers 12 and 18 on the left and right side of the
fuselage, in accordance with Avro International Aerospace Inspection
Service Bulletin S.B. 53-131, dated March 29, 1995. If the polymer
coating on frame 29 prevents a detailed visual inspection, perform a
surface eddy current inspection for cracking in accordance with the
service bulletin. Perform the inspections at the time specified in
paragraph (a)(1), (a)(2), or (a)(3) of this AD, as applicable.
(1) For Model Avro 146-RJ100A airplanes on which British
Aerospace Modification HCM01411A, HCM01411B, or HCM01411C has not
been accomplished: Perform the inspection within 6 months after the
effective date of this AD, or prior to the accumulation of 12,000
total landings, whichever occurs later. Repeat the inspection
thereafter at intervals not to exceed 4,000 landings.
(2) For Model Avro 146-RJ70A and -RJ85A airplanes on which
British Aerospace Modification HCM01411A or HCM01411C has not been
accomplished: Perform the inspection within 6 months after the
effective date of this AD, or prior to the accumulation of 24,000
total landings, whichever occurs later. Repeat the inspection
thereafter at intervals not to exceed 4,000 landings.
(3) For Model Avro 146-RJ100A airplanes on which British
Aerospace Modification HCM01411C has been accomplished, but on which
British Aerospace Modification HCM01411A or HCM01411B has not been
accomplished: Perform the inspection within 6 months after the
effective date of this AD, or prior to the accumulation of 68,000
total landings, whichever occurs later. Repeat the inspection
thereafter at intervals not to exceed 4,000 landings.
(b) If any cracking is found during any inspection required by
paragraph (a) of this AD: Prior to further flight, repair in
accordance with a method approved by the Manager, Standardization
Branch, ANM-113, FAA, Transport Airplane Directorate.
(c) Accomplishment of the modification of each affected bolt
position in accordance with Avro International Aerospace Inspection
Service Bulletin S.B. 53-131, dated March 29, 1995, prior to the
embodiment times shown in Table ``A'' of that service bulletin,
constitutes terminating action for the repetitive inspections
required by paragraph (a) of this AD.
Note 2: Avro Repair Instruction Leaflet (RIL) HC536H9168
provides detailed instructions for modification of all bolt
positions in the affected areas of frame 29.
(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.
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 3: 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.
[[Page 41039]]
Issued in Renton, Washington, on August 1, 1996.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-20073 Filed 8-6-96; 8:45 am]
BILLING CODE 4910-13-U