[Federal Register: October 28, 2004 (Volume 69, Number 208)]
[Rules and Regulations]
[Page 62803-62805]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr28oc04-2]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-173-AD; Amendment 39-13832; AD 2004-22-04]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-400, -400D, and -400F
Series Airplanes Equipped With General Electric (GE) or Pratt & Whitney
(P&W) Series Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Boeing Model 747-400, -400D, and -400F series
airplanes, equipped with GE or P&W series engines. This amendment
requires modifications and functional tests of the wiring of the wire
integration unit and the air supply control test unit (ASCTU) of the
engine bleed air distribution system. The actions specified by this AD
are intended to prevent inadvertent commanded shutdown of the engine
bleed air distribution systems due to an erroneous ASCTU command. This
type of shutdown could cause depressurization of the airplane and
subsequent ice build-up on the engine inlets during descent, which
could result in ingestion of ice into the
[[Page 62804]]
engine(s) and consequent loss of thrust on one or more engines. This
action is intended to address the identified unsafe condition.
DATES: Effective December 2, 2004.
The incorporation by reference of a certain publication listed in
the regulations is approved by the Director of the Federal Register as
of December 2, 2004.
ADDRESSES: The service information referenced in this AD may be
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle,
Washington 98124-2207. This information may be examined at the Federal
Aviation Administration (FAA), Transport Airplane Directorate, Rules
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the National
Archives and Records Administration (NARA). For information on the
availability of this material at NARA, call (202) 741-6030, or go to:
http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
FOR FURTHER INFORMATION CONTACT: Don Eiford, Aerospace Engineer,
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (425) 917-6465; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Boeing Model 747-400, -
400D, and -400F series airplanes, equipped with GE or P&W series
engines, was published as a supplemental notice of proposed rulemaking
(NPRM) in the Federal Register on August 16, 2004 (69 FR 50341). That
action proposed to require modifications and functional tests of the
wiring of the wire integration unit and the air supply control test
unit of the engine bleed air distribution system.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule as proposed.
Cost Impact
There are approximately 414 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 70 airplanes of U.S. registry
will be affected by this AD, that it will take approximately 8 work
hours per airplane to accomplish the required actions, and that the
average labor rate is $65 per work hour. Required parts will be
minimal. Based on these figures, the cost impact of the AD on U.S.
operators is estimated to be $36,400, or $520 per airplane.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the requirements of this AD
action, and that no operator would accomplish those actions in the
future if this AD were not adopted. The cost impact figures discussed
in AD rulemaking actions represent only the time necessary to perform
the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.
Regulatory Impact
The regulations adopted herein will not have a substantial direct
effect 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, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
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
0
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
0
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]
0
2. Section 39.13 is amended by adding the following new airworthiness
directive:
2004-22-04 Boeing: Amendment 39-13832. Docket 2002-NM-173-AD.
Applicability: Model 747-400, -400D, and -400F series airplanes;
as listed in Boeing Service Bulletin 747-36A2136, Revision 2, dated
May 13, 2004; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent inadvertent commanded shutdown of the engine bleed
air distribution systems due to an erroneous air supply control test
unit (ASCTU) command, which could cause depressurization of the
airplane and subsequent ice build-up on the engine inlets during
descent, which could result in ingestion of ice into the engine(s)
and consequent loss of thrust on one or more engines; accomplish the
following:
Modifications/Tests
(a) Within 18 months after the effective date of this AD: Do the
modifications and functional tests of the wiring of the wire
integration unit (WIU) and the ASCTU of the engine bleed air
distribution system specified in paragraphs (a)(1), (a)(2), (a)(3),
and (a)(4) of this AD, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747-36A2136, Revision 2,
dated May 13, 2004. Before further flight after accomplishing
paragraphs (a)(2), (a)(3), and (a)(4) of this AD: Do the post-
installation tests in accordance with the service bulletin.
(1) Remove the existing ASCTU.
(2) Do the wiring changes between the WIU and ASCTU and the
wiring changes to the WIU.
(3) Do the resistance tests.
(4) Install a new or reworked ASCTU.
Credit for Previous Issues of Boeing Service Bulletin
(b) Modifications and tests accomplished before the effective
date of this AD in accordance with Boeing Alert Service Bulletin
747-36A2136, dated April 12, 2001; or Revision 1, dated January 17,
2002; are considered acceptable for compliance with the
corresponding actions specified in paragraph (a) of this AD, if the
resistance tests were done with the ASCTU removed. If the resistance
tests were done with the ASCTU installed, do the actions specified
in paragraphs (b)(1), (b)(2), and (b)(3) of this AD, at the time
specified in paragraph (a) of this AD, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 747-36A2136,
Revision 2, dated May 13, 2004. Before further flight after
accomplishing paragraph (b)(3) of this AD: Do the post-installation
tests in accordance with the service bulletin.
(1) Remove the existing ASCTU.
[[Page 62805]]
(2) Do the resistance tests.
(3) Reinstall the ASCTU.
Part Installation
(c) As of the effective date of this AD, no person may install
on any airplane an ASCTU having a part number listed in the ``Old
Part Number'' column in the table specified in paragraph 3.C. of the
Accomplishment Instructions of Hamilton Sundstrand Service Bulletin
36-186, dated March 30, 2001.
Alternative Methods of Compliance (AMOCs)
(d) The Manager, Seattle Aircraft Certification Office, FAA, has
the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
Incorporation by Reference
(e) Unless otherwise specified in this AD, the actions shall be
done in accordance with Boeing Service Bulletin 747-36A2136,
Revision 2, dated May 13, 2004. 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
Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington
98124-2207. Copies may be inspected at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call (202) 741-6030,
or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Effective Date
(f) This amendment becomes effective on December 2, 2004.
Issued in Renton, Washington, on October 18, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-24030 Filed 10-27-04; 8:45 am]
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