[Federal Register Volume 62, Number 35 (Friday, February 21, 1997)]
[Rules and Regulations]
[Pages 7932-7934]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-4098]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-ANE-15; Amendment 39-9927; AD 97-04-04]
RIN 2120-AA64
Airworthiness Directives; AlliedSignal Inc. GTCP85 Series
Auxiliary Power Units
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to AlliedSignal Inc. (formerly Garrett Auxiliary Power
Division) GTCP85 Series auxiliary power units (APUs), that currently
requires removing the existing turbine wheel shroud and installing one
constructed of Hastelloy ``S'' material, or installing a containment
augmentation ring. This amendment deletes the option of installing a
turbine shroud constructed of Hastelloy ``S'' material. This amendment
is prompted by a report of insufficient APU containment capability with
the Hastelloy ``S'' shroud alone installed. The actions specified by
this AD are intended to prevent turbine shroud fragments from exiting
the APU and puncturing the APU compartment, which could result in
reduced fire extinguishing capability in the APU compartment.
DATES: Effective March 24, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 24, 1997.
ADDRESSES: The service information referenced in this AD may be
obtained from AlliedSignal Aerospace, Attn: Data Distribution, M/S 64-
3/2101-201, P.O. Box 29003, Phoenix, AZ 85038-9003; telephone (602)
365-2493, fax (602) 365-5577. This information may be examined at the
Federal Aviation Administration (FAA), New England Region, Office of
the Assistant Chief Counsel, 12 New England Executive Park, Burlington,
MA 01803-5299; or at the Office of the Federal Register, 800 North
Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Robert Baitoo, Aerospace Engineer, Los
Angeles Aircraft Certification Office, FAA, Transport Airplane
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; telephone
(310) 627-5245; fax (310) 627-5210.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 93-07-13,
Amendment 39-8545 (58 FR 21917, April 26, 1993), which is applicable to
AlliedSignal Inc. (formerly Garrett Auxiliary Power Division) GTCP85
Series auxiliary power units (APUs), was published in the Federal
Register on August 12, 1996 (61 FR 41751). That action proposed to
require installing an improved containment augmentation ring, Part
Number (P/N) 3616426-1, or P/N 3616426-3, which is a redesigned
containment augmentation ring to allow installation on certain APUs
that cannot accept the -1 containment augmentation ring. The
containment augmentation rings, P/Ns 3616426-1 and 3616426-3, improve
the containment capability of the APU relative to the earlier
containment augmentation ring, P/N 3612249-1, by preventing turbine
shroud fragments from passing around the containment augmentation ring.
The installation must be accomplished within 24 months after the
effective date of this AD, for flight operable APUs, and within 36
months after the effective date of this AD, for APUs that are operable
on the ground only. The actions would be required to be accomplished in
accordance with AlliedSignal Aerospace Alert Service Bulletin (ASB) No.
[[Page 7933]]
GTCP85-49-A7189, Revision 2, dated October 8, 1996, AlliedSignal
Aerospace ASB No. GTCP85-49-A7189, Revision 1, dated July 19, 1996, or
AlliedSignal Aerospace ASB No. GTCP85-49-A7189, Original, dated March
29, 1996; and AlliedSignal Aerospace ASB No. GTCP85-49-A6706, Revision
2, dated November 28, 1994, AlliedSignal Aerospace ASB No. GTCP85-49-
A6706, Revision 1, dated November 12, 1993, or Garrett ASB No. GTCP85-
49-A6706, Original, dated December 7, 1992.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
One commenter states that the AD should apply only to APUs with
one-piece cast turbine wheels made of MAR-M-247 material, as only these
type turbine wheels have failed in the commenter's experience. The FAA
concurs in part. The proposed rule as written applies to APUs with one-
piece cast turbine wheels with the listed P/Ns, which are made of MAR-
M-247 material, but also Inconel, which have failed as well.
Two commenters state that the AD should add an additional method of
compliance by replacing the one-piece cast turbine wheels with two-
piece wheels. The FAA does not concur. The proposed AD does not apply
to APUs with two-piece turbine wheels.
One commenter (the manufacturer) states that the economic analysis
provides figures for the number of APUs in service domestically and
worldwide that are too low. The FAA concurs and revised the economic
analysis of this final rule accordingly.
One commenter states that the proposed AD should be more clear in
stating that compliance is acceptable with either ASB stated in
paragraphs (a)(1) and (a)(2) and (b)(1) and (b)(2) of the compliance
section. The FAA concurs and has put the ``or'' between the appropriate
paragraphs in bold type to highlight its significance.
Two commenters concur with the AD as proposed.
Since publication of the proposed rule, AlliedSignal Aerospace has
issued Revision 2 to ASB No. GTCP85-49-A7189, dated October 8, 1996,
which is referenced in this final rule along with Revision 1, dated
July 19, 1996, and Original, dated March 29, 1996. These revisions of
that ASB are all approved methods of compliance for the appropriate
paragraphs of this AD.
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes described
previously. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
There are approximately 4,100 APUs of the affected design in the
worldwide fleet. The FAA estimates that 1,300 APUs installed on
aircraft of U.S. registry will be affected by this AD, that it will
take no additional work hours if the required actions are accomplished
when the APU is already disassembled in the shop. Required parts will
cost approximately $1,550 per APU. Based on these figures, the total
cost impact of the AD on U.S. operators is estimated to be $2,015,000.
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.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it 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 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment 39-8545 (52 FR
45163, November 25, 1987) and by adding a new airworthiness directive,
Amendment 39-9927, to read as follows:
97-04-04 AlliedSignal Inc.: Amendment 39-9927. Docket 96-ANE-15.
Supersedes AD 93-07-13, Amendment 39-8545.
Applicability: AlliedSignal Inc. (formerly Garrett Auxiliary
Power Division) GTCP85 series auxiliary power units (APUs),
incorporating a one-piece cast turbine wheel, Part Numbers (P/Ns)
968095-X, 3604604-X, 3606982-1, or 3842072-X (where ``X'' denotes
any number). These APUs are installed on but not limited to the
following aircraft: British Aerospace BAC 1-11 series; Boeing 707,
727, and 737 series; Lockheed L382 series; and McDonnell Douglas DC-
8-70, DC-9, and MD-88 series aircraft.
Note 1: This airworthiness directive (AD) applies to each APU
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 APUs 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 (c) 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 turbine shroud fragments from exiting the APU and
puncturing the APU compartment, which could result in reduced fire
extinguishing capability in the APU compartment, accomplish the
following:
(a) For flight operable APUs, within 24 months after the
effective date of this AD, accomplish either of the following:
(1) Install a containment augmentation ring, P/N 3616426-3, in
accordance with AlliedSignal Aerospace Alert Service Bulletin (ASB)
No. GTCP85-49-A7189, Revision 2, dated October 8, 1996, Revision 1,
dated July 19, 1996, or Original, dated March 29, 1996; or
(2) Install a containment augmentation ring, P/N 3616426-1, in
accordance with AlliedSignal Aerospace ASB No.GTCP85-49-A6706,
Revision 2, dated November 28, 1994, AlliedSignal Aerospace ASB No.
GTCP85-49-A6706, Revision 1, dated November 12, 1993, or Garrett ASB
No. GTCP85-49-A6706, Original, dated December 7, 1992.
(b) For APUs that are operable on the ground only, within 36
months after the effective date of this AD, accomplish either of the
following:
(1) Install a containment augmentation ring, P/N 3616426-3, in
accordance with AlliedSignal Aerospace ASB No. GTCP85-
[[Page 7934]]
49-A7189, Revision 2, dated October 8, 1996, Revision 1, dated July
19, 1996, or Original, dated March 29, 1996; or
(2) Install a containment augmentation ring, P/N 3616426-1, in
accordance with AlliedSignal Aerospace ASB No. GTCP85-49-A6706,
Revision 2, dated November 28, 1994, AlliedSignal Aerospace ASB No.
GTCP85-49-A6706, Revision 1, dated November 12, 1993, or Garrett ASB
No. GTCP85-49-A6706, Original, dated December 7, 1992.
(c) 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, Los Angeles Aircraft Certification
Office. The request should be forwarded through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Los Angeles Aircraft Certification Office.
Note 2: Information concerning the existence of approved
alternative method of compliance with this AD, if any, may be
obtained from the Los Angeles Aircraft Certification Office.
(d) 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 aircraft to a location where
the requirements of this AD can be accomplished.
(e) The actions required by this AD shall be done in accordance
with the following ASBs:
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Document No. Pages Revision Date
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AlliedSignal Aerospace, GTCP85-49- 1-14............... 2......................... Oct. 8, 1996.
A7189.
Total pages: 14.
AlliedSignal Aerospace, GTCP85-49- 1-12............... 1......................... July 19, 1996.
A7189.
Total pages: 12.
AlliedSignal Aerospace, GTCP85-49- 1-10............... Original.................. Mar. 29, 1996.
A7189.
Total pages: 10.
AlliedSignal Aerospace, GTCP85-49- 1.................. 2......................... Nov. 28, 1994.
A6706.
2, 3............... 1......................... Nov. 12, 1993.
4.................. 2......................... Nov. 28, 1994.
5-8................ 1......................... Nov. 12, 1993.
9, 10.............. 2......................... Nov. 28, 1994.
Total pages: 10.
AlliedSignal Aerospace GTCP85-49- 1-10............... 1......................... Nov. 12, 1993
A6706
Total pages: 10.
Garrett GTCP85-49-A6706............ 1, 2............... Original.................. Dec. 7, 1992
4-10............... Original.................. Dec. 7, 1992.
Total pages: 9.
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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 AlliedSignal Aerospace, Attn:
Data Distribution, M/S 64-3/2101-201, P.O. Box 29003, Phoenix, AZ
85038-9003; telephone (602) 365-2493, fax (602) 365-5577. Copies may
be inspected at the FAA, New England Region, Office of the Assistant
Chief Counsel, 12 New England Executive Park, Burlington, MA; or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
Suite 700, Washington, DC.
(f) This amendment becomes effective on March 24, 1997.
Issued in Burlington, Massachusetts, on February 4, 1997.
James C. Jones,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 97-4098 Filed 2-20-97; 8:45 am]
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