[Federal Register Volume 64, Number 236 (Thursday, December 9, 1999)]
[Proposed Rules]
[Pages 68956-68958]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-31874]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-174-AD]
RIN 2120-AA64
Airworthiness Directives; British Aerospace Model BAe 146-100A, -
200A, and -300A Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of an existing
airworthiness directive (AD), applicable to all British Aerospace Model
BAe 146-100A, -200A, and -300A series airplanes, that currently
requires installation of a placard prescribing special procedures to be
followed when operating at certain flight levels with the engine and
airframe anti-ice switch ON; modification of the air brake auto-retract
function; a revision to the Airplane Flight Manual (AFM) relative to
altitude and operating limitations associated with flight in icing
conditions above 26,000 feet. That AD was prompted by reports of
uncommanded engine thrust reductions (rollback) when operating in
certain icing conditions that exist in the vicinity of thunderstorms.
This action would add a requirement for the installation/replacement of
new placards. This proposal also would provide for an optional
terminating modification for the AFM revision and installation/
replacement of placards. The actions specified by the proposed AD are
intended to prevent engine power rollback during flight in icing
conditions, a condition that could result in insufficient power to
sustain flight.
DATES: Comments must be received by January 10, 2000.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-174-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from British Aerospace Regional Aircraft American Support,
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-174-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-174-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On July 10, 1996, the FAA issued AD 96-14-09, amendment 39-9694 (61
FR 37199, July 17, 1996), applicable to all British Aerospace Model BAe
146-100A, -200A, and -300A series airplanes, to require installation of
a placard prescribing special procedures to be followed when operating
at certain flight levels with the engine and airframe anti-ice switch
ON; modification of the air brake auto-retract function; and a revision
to the Airplane
[[Page 68957]]
Flight Manual (AFM) relative to altitude and operating limitations
associated with flight in icing conditions above 26,000 feet. That
action was prompted by reports of uncommanded engine thrust reductions
(rollback) when operating in certain icing conditions that exist in the
vicinity of thunderstorms. The requirements of that AD are intended to
prevent engine power rollback during flight in icing conditions, a
condition that could result in insufficient power to sustain flight.
Actions Since Issuance of Previous Rule
Since the issuance of that AD, British Aerospace has issued Service
Bulletin SB.11-137-30405A, dated March 26, 1998, which describes
procedures for installation of a placard on the flight deck to indicate
that a 26,000 feet altitude limitation in icing is applicable, and
replacement of a certain ice protection panel placard with a new
placard for N2 limitations.
British Aerospace also has issued Service Bulletin SB.71-72-30473A,
dated July 8, 1998, and Revision 1, dated November 2, 1998, which
describes procedures for modification of all four engines. These
modifications include:
Reduction of the length core-flow/ fan-flow splitter (cut-
back splitter) to reduce ice crystal/water ingestion to the core;
Modification of the splitter lip insulating baffle to
reduce heat loss;
Installation of a heated exit guide vane (EGV) to prevent
ice build up;
Relocation of the engine anti-ice air source to the
combustor bleed plenum to reduce system heat loss;
Installation of a new anti-ice valve with improved
couplings; and
Modification of plumbing to install improved insulated
connections.
The service bulletin also describes certain revisions to the AFM
for operation of the airplane following installation of modified
engines. Accomplishment of the modification on all four engines and
insertion of the AFM revisions would eliminate the need for the
installation/replacement of the placards described in Service Bulletin
SB.11-137-30405A.
The FAA has issued AD 99-15-06, amendment 39-11225 (64 FR 38557,
July 19, 1999), applicable to AlliedSignal Inc. Model ALF502R-5 and
ALF502R-3A turbofan engines, to require incorporation of an improved
fan core inlet anti-ice system (i.e., modification of those engines in
accordance with Service Bulletin SB.71-72-30473A). The actions
specified in that AD are intended to prevent ice accretion on the fan
core inlet stator vane surfaces, which can result in engine rollback
and loss of thrust control in icing conditions. Operators should note
that Service Bulletin SB.71-72-30473A only reflects procedures for
installation of engines that have been modified in accordance with the
requirements of AD 99-15-06.
Accomplishment of the actions specified in Service Bulletin SB.11-
137-30405A is intended to adequately address the identified unsafe
condition. The Civil Aviation Authority (CAA), which is the
airworthiness authority for the United Kingdom, classified Service
Bulletin SB.11-137-30405A as mandatory, approved Service Bulletin
SB.71-72-30473A, and issued British airworthiness directives 004-03-98
and 003-06-96, Revision 1, 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 supersede AD 96-14-09 to
continue to require modification of the air brake auto-retract
function; and a revision to the AFM relative to altitude and operating
limitations associated with flight in icing conditions above 26,000
feet. In addition, the proposed AD would require accomplishment of the
actions specified in British Aerospace Service Bulletin SB.11-137-
30405A, described previously. The proposal also would provide for an
optional terminating modification for the AFM revision and
installation/replacement of placards.
Cost Impact
There are approximately 40 airplanes of U.S. registry that would be
affected by this proposed AD.
The actions that are currently required by AD 96-14-09, and
retained in this proposed AD, take approximately 4 work hours per
airplane to accomplish, at an average labor rate of $60 per work hour.
Based on these figures, the cost impact of the currently required
actions on U.S. operators is estimated to be $9,600, or $240 per
airplane.
The new actions that are proposed in this AD action would take
approximately 1 work hour per airplane to accomplish, at an average
labor rate of $60 per work hour. Based on these figures, the cost
impact of the new proposed requirements of this AD on U.S. operators is
estimated to be $2,400, or $60 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the current or proposed
requirements of this AD action, and that no operator would accomplish
those actions in the future if this AD were not adopted.
Should an operator elect to accomplish the actions associated with
the optional terminating modification, it would take approximately 34
work hours per airplane to accomplish, at an average labor rate of $60
per work hour. Required parts would cost approximately $2,400 per
airplane. Based on these figures, the cost impact of the proposed
optional terminating modification is estimated to be $4,440 per
airplane.
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
[[Page 68958]]
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 removing amendment 39-9694 (61 FR
37199, July 17, 1996), and by adding a new airworthiness directive
(AD), to read as follows:
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-174-AD. Supersedes AD 96-14-09, Amendment 39-
9694.
Applicability: All Model BAe 146-100A, -200A, and -300A 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 (g)(1)
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 engine power rollback during flight in icing
conditions, a condition that could result in insufficient power to
sustain flight, accomplish the following:
Restatement of Requirements of AD 96-14-09, Amendment 39-9694
Placard Installation
(a) For airplanes listed in British Aerospace Service Bulletin
SB.11-97-012858A, Revision 1, dated April 3, 1992: Within 30 days
after December 17, 1992 (the effective date of AD 92-24-09,
amendment 39-8415), install a placard below the ice protection
switches on the flight deck overhead panel to include additional
procedures to be followed when operating at certain flight levels
with the engine and airframe anti-ice switch ON, in accordance with
British Aerospace Service Bulletin SB.11-97-01285A, Revision 1,
dated April 3, 1992.
Modification
(b) For airplanes listed in British Aerospace Service Bulletin
SB.11-97-01285A, Revision 1, dated April 3, 1992: Within 30 days
after December 17, 1992 (the effective date of AD 92-24-09,
amendment 39-8415), modify the air brake auto-retract function, in
accordance with British Aerospace Service Bulletin SB.11-97-01285A,
Revision 1, dated April 3, 1992.
Airplane Flight Manual Revision
(c) Within 6 days after July 22, 1996 (the effective date of AD
96-14-09, amendment 39-9694), amend the FAA-approved Airplane Flight
Manual (AFM) as required by paragraphs (c)(1) and (c)(2) of this AD.
(1) Remove the following Temporary Revisions (TR) from the
Limitations Section and Normal/Abnormal Procedures Section, as
applicable:
(i) For Model BAe 146-100A series airplanes: TR 30, Issue No. 2
(Document No. BAe 3.3), dated February 1994.
(ii) For Model BAe 146-200A series airplanes: TR 41, Issue No. 2
(Document No. BAe 3.3), dated February 1994, or TR 42, Issue No. 2
(Document No. BAe 3.3), dated February 1994, as applicable.
(iii) For Model BAe 146-300A series airplanes: TR 23, Issue No.
2 (Document No. BAe 3.3), dated February 1994.
(2) Insert the following TR's into the Limitations Section and
the Normal/Abnormal Procedures/Handling Section, as applicable.
(i) For Model BAe 146-100A series airplanes: TR 32, Issue No. 2
(Document BAe 3.3), dated July 1996.
(ii) For Model BAe 146-200A series airplanes: TR 44, Issue No. 2
(Document BAe 3.6), dated July 1996.
(iii) For Model BAe 146-300A series airplanes: TR 25, Issue No.
2 (Document BAe 3.11), dated July 1996.
(d) When the TR's specified in paragraph (c)(2) have been
incorporated into an AFM General Revision, the applicable AFM
General Revision may be inserted into the corresponding FAA-approved
AFM, provided the information contained in the AFM General Revision
corresponds identically to that specified in TR 32, TR 44, or TR 25.
New Requirements of this AD
Placard Installation
(e) Within 30 days after the effective date of this AD, install
a placard on the flight deck to indicate that a 26,000 feet altitude
limitation in icing is applicable, and replace the ice protection
panel placard with a new placard for N2 limitations, in accordance
with British Aerospace Service Bulletin SB.11-137-30405A, dated
March 26, 1998. Upon accomplishment of this placard installation,
the placard required by paragraph (a) of this AD may be removed.
Optional Terminating Modification
(f) Modification of all four engines [i.e., reduction of the
length core-flow/fan-flow splitter (cut-back splitter); modification
of the splitter lip insulating baffle; installation of a heated exit
guide vane (EGV); relocation of the engine anti-ice air source to
the combustor bleed plenum; installation of a new anti-ice valve
with improved couplings; and installation of improved insulated
connections], and insertions of AFM revisions, in accordance with
British Aerospace Service Bulletin SB.71-72-30473A, dated July 8,
1998, or Revision 1, dated November 2, 1998; constitutes terminating
action for the requirements of this AD. After the modification is
accomplished, the AFM revisions and placards required by paragraphs
(c), (d), and (e) of this AD may be removed.
Note 2: British Aerospace Service Bulletin SB.71-72-30473A,
dated July 8, 1998, and Revision 1, dated November 2, 1998, only
describes procedures for installation of engines that have been
modified in accordance with the requirements of AD 99-15-06,
amendment 39-11225.
Alternative Methods of Compliance
(g)(1) 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(2) Alternative methods of compliance, approved previously in
accordance with AD 96-14-09, amendment 39-9694, are approved as
alternative methods of compliance with this AD.
Special Flight Permits
(h) 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 4: The subject of this AD is addressed in British
airworthiness directives 004-03-98 and 003-06-96, Revision 1.
Issued in Renton, Washington, on December 3, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-31874 Filed 12-8-99; 8:45 am]
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