[Federal Register: August 27, 2003 (Volume 68, Number 166)]
[Rules and Regulations]
[Page 51439-51445]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr27au03-3]
[[Page 51439]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-128-AD; Amendment 39-13269; AD 2003-16-16]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-400 Series Airplanes
Equipped With General Electric Model CF6-80C2 Series Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain Boeing Model 747-400 series airplanes, that
currently requires repetitive tests of the cone brake of the central
drive unit (CDU) of the thrust reversers, and corrective actions if
necessary. This amendment requires installation of a thrust reverser
actuation system (TRAS) lock and various related modifications and
installations. Following installation of the TRAS lock, this action
also requires repetitive functional tests of the TRAS lock, and
corrective action if necessary. These actions are intended to prevent
an inadvertent deployment of a thrust reverser during flight, which
could result in loss of control of the airplane.
DATES: Effective October 1, 2003.
The incorporation by reference of certain publications, as listed
in the regulations, is approved by the Director of the Federal Register
as of October 1, 2003.
The incorporation by reference of certain other publications, as
listed in the regulations, was approved previously by the Director of
the Federal Register as of September 6, 2000 (65 FR 47252, August 2,
2000).
The incorporation by reference of certain other publications, as
listed in the regulations, was approved previously by the Director of
the Federal Register as of March 13, 2000 (65 FR 5742, February 7,
2000).
The incorporation by reference of certain other publications, as
listed in the regulations, was approved previously by the Director of
the Federal Register as of August 25, 1999 (64 FR 39003, July 21,
1999).
ADDRESSES: The service information referenced in this AD may be
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle,
Washington 98124-2207; and Distribution, Lockheed Martin Technical
Services, 1330 Kemper Meadow Drive, suite 110-C, Cincinnati, Ohio
45240. 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 Office of the
Federal Register, 800 North Capitol Street, NW., suite 700, Washington,
DC.
FOR FURTHER INFORMATION CONTACT: Sulmo Mariano, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone
(425) 917-6501; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 2000-09-03,
amendment 39-11711 (65 FR 25829, May 4, 2000), which is applicable to
certain Boeing Model 747-400 series airplanes, was published in the
Federal Register on January 30, 2003 (68 FR 4731). The action proposed
to continue to require repetitive tests of the cone brake of the
central drive unit of the thrust reversers, and corrective actions if
necessary. The action proposed to add new requirements for installation
of a thrust reverser actuation system (TRAS) lock and various related
modifications and installations. The action also proposed to require,
following installation of the TRAS lock, repetitive functional tests of
the TRAS lock, and corrective action if necessary.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received from a single commenter.
Request To Add Additional Sources of Service Information
The commenter notes that there are later revisions available for
certain service bulletins referenced in the proposed AD. The commenter
points out the following:
[sbull] Lockheed Martin is now Middle River Aircraft Systems
(MRAS).
[sbull] Lockheed Martin Service Bulletin 78-1007, Revision 1, dated
March 18, 1997, has been superseded by MRAS Service Bulletin 78-1007,
Revision 2, dated March 10, 1998.
[sbull] Lockheed Martin Service Bulletin 78-1020, Revision 2, dated
March 20, 1997, has been superseded by MRAS Service Bulletin 78-1020,
Revision 3, dated March 16, 1998; and MRAS CF6-80C2B Service Bulletin
78-1020, Revision 4, dated October 10, 2002.
The commenter notes that no additional work is necessary per the new
revisions of the service bulletins.
We infer that the commenter is requesting that we revise the final
rule to include references to the later revisions of the service
bulletins. We concur and have revised paragraphs (d)(2)(i) and
(d)(2)(iii) of this AD to reference the service bulletin revisions
cited by the commenter as additional acceptable sources of service
information.
Request To Accept Additional Software Versions
The same commenter notes that Boeing Service Bulletin 747-31-2242,
dated April 18, 1996, which is cited in paragraph (d)(2)(iv) of the
proposed AD, specifies installation of integrated display system (IDS)
software version 995-0017-012. The commenter similarly notes that
Boeing Service Bulletin 747-45-2016 (Revision 1, dated May 2, 1996),
which is cited in paragraph (d)(2)(v) of the proposed AD, specifies
installation of central maintenance computer (CMC) software version
685-2270-009. The commenter points out that, since the issuance of
those service bulletins, the manufacturer has released several
additional software versions. The commenter requests that we include
the additional software versions as acceptable parts for the purposes
of the proposed AD.
We concur and have added references to acceptable versions of the
IDS and CMC software into paragraphs (d)(2)(iv) and (d)(2)(v) of this
AD, respectively. We note, however, that the manufacturer has delayed
release of one of the CMC software versions to which the commenter
refers, 685-2270-012. Because we are unable to determine whether that
version would be acceptable for compliance with this AD, this final
rule does not refer to that version.
Conclusion
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 previously
described. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Changes to 14 CFR Part 39/Effect on the AD
On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002), which governs the
[[Page 51440]]
FAA's airworthiness directives system. The regulation now includes
material that relates to altered products, special flight permits, and
alternative methods of compliance. Because we have now included this
material in part 39, we no longer need to include it in each individual
AD. However, for clarity and consistency in this final rule, we have
retained the language of the NPRM regarding that material.
Change to Labor Rate Estimate
Since we issued the proposed AD, we have reviewed the figures we
have used over the past several years to calculate AD costs to
operators. To account for various inflationary costs in the airline
industry, we find it necessary to increase the labor rate used in these
calculations from $60 per work hour to $65 per work hour. The cost
impact information, below, reflects this increase in the specified
hourly labor rate.
Cost Impact
There are approximately 145 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 8 airplanes of U.S. registry
will be affected by this AD.
The functional test that is currently required by AD 2000-09-03
takes approximately 12 work hours per airplane to accomplish, at an
average labor rate of $65 per work hour. Based on these figures, the
cost impact of the currently required actions on U.S. operators is
estimated to be $6,240, or $780 per airplane, per test cycle.
The installations in Boeing Service Bulletin 747-78-2151, Revision
2, will take approximately 410 work hours per airplane to accomplish,
at an average labor rate of $65 per work hour. Required parts will be
provided at no charge. Based on these figures, the cost impact of this
requirement on U.S. operators is estimated to be $213,200, or $26,650
per airplane.
The installation specified in Lockheed Martin Service Bulletin 78-
1007, Revision 1, or MRAS Service Bulletin 78-1007, Revision 2, will
take approximately 60 work hours per airplane to accomplish, at an
average labor rate of $65 per work hour. Required parts will be
provided at no charge. Based on these figures, the cost impact of this
requirement on U.S. operators is estimated to be $31,200, or $3,900 per
airplane.
The installation specified in Boeing Service Bulletin 747-78-2132,
Revision 2, will take approximately 223 work hours per airplane to
accomplish, at an average labor rate of $65 per work hour. Required
parts will cost between $32,219 and $36,562 per airplane. Based on
these figures, the cost impact of this requirement is estimated to be
between $46,714 and $51,057 per airplane. The manufacturer may cover
the cost of replacement parts associated with this service bulletin,
subject to warranty conditions. As a result, the costs attributable to
this required action may be less than stated above.
The installation specified in Lockheed Martin Service Bulletin 78-
1020, Revision 2, or MRAS Service Bulletin 78-1020, Revision 3 or 4,
will take approximately 16 work hours per airplane to accomplish, at an
average labor rate of $65 per work hour. Required parts will be
provided at no charge. Based on these figures, the cost impact of this
requirement on U.S. operators is estimated to be $8,320, or $1,040 per
airplane.
The installation specified in Boeing Service Bulletin 747-31-2242
will take approximately 2 work hours per airplane to accomplish, at an
average labor rate of $65 per work hour. The cost of required parts
will be negligible. Based on these figures, the cost impact of this
requirement is estimated to be $1,040, or $130 per airplane. The
manufacturer may cover the cost of replacement parts and labor costs
associated with accomplishment of this service bulletin, subject to
warranty conditions. As a result, the costs attributable to this
required action may be less than stated.
The installation specified in Boeing Service Bulletin 747-45-2016,
Revision 1, will take approximately 3 work hours per airplane to
accomplish, at an average labor rate of $65 per work hour. The cost of
required parts will be negligible. Based on these figures, the cost
impact of this requirement is estimated to be $1,560, or $195 per
airplane. The manufacturer may cover the labor costs associated with
accomplishment of this service bulletin, subject to warranty
conditions. As a result, the costs attributable to this required action
may be less than stated above.
The functional test that will be required following installation of
the TRAS lock would take approximately 12 work hours per airplane to
accomplish, at an average labor rate of $65 per work hour. Based on
these figures, the cost impact of this requirement is estimated to be
$6,240, or $780 per airplane, per test cycle.
The cost impact figures discussed above are 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 removing amendment 39-11711 (65 FR
25829, May 4, 2000), and by adding a new airworthiness directive (AD),
amendment 39-13269, to read as follows:
2003-16-16 Boeing: Amendment 39-13269. Docket 2002-NM-128-AD.
Supersedes AD 2000-09-03, Amendment 39-11711.
[[Page 51441]]
Applicability: Model 747-400 series airplanes equipped with
General Electric (GE) Model CF6-80C2 series engines, 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 (h)(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 an inadvertent deployment of a thrust reverser during
flight, which could result in loss of control of the airplane,
accomplish the following:
Requirements of AD 2000-09-03
Repetitive Functional Tests
(a) Within 1,000 hours time-in-service after the most recent
test of the center drive unit (CDU) cone brake as specified in
paragraph (b)(1) of AD 94-15-05, amendment 39-8976; or within 650
hours time-in-service after May 19, 2000 (the effective date of AD
2000-09-03, amendment 39-11711); whichever occurs later: Perform a
functional test to detect discrepancies of the CDU cone brake on
each thrust reverser as specified in paragraph (a)(1) or (a)(2) of
this AD, as applicable.
(1) For Model 747-400 series airplanes equipped with thrust
reversers that have not been modified in accordance with Boeing
Service Bulletin 747-78-2151 or a production equivalent: Perform the
test in accordance with Boeing Service Bulletin 747-78A2166,
Revision 1, dated October 9, 1997; or paragraph 3.C. of Boeing Alert
Service Bulletin 747-78A2166, Revision 2, dated March 15, 2001; or
the applicable section of paragraph III.A. of the Accomplishment
Instructions of Boeing Service Bulletin 747-78A2113, Revision 2,
dated June 8, 1995; or Revision 3, dated September 11, 1997. Repeat
the test thereafter at intervals not to exceed 650 hours time-in-
service.
(2) For Model 747-400 series airplanes equipped with thrust
reversers that have been modified in accordance with Boeing Service
Bulletin 747-78-2151 or a production equivalent: Perform the test in
accordance with Appendix 1 (including Figure 1) of this AD, or
paragraph 3.C. of Boeing Alert Service Bulletin 747-78A2166,
Revision 2, dated March 15, 2001. After the effective date of this
AD, only Boeing Alert Service Bulletin 747-78A2166, Revision 2, may
be used. Repeat the test thereafter at intervals not to exceed 1,000
hours time-in-service.
Note 2: Accomplishment of the CDU cone brake test during
production in accordance with Production Revision Record (PRR)
80452-102 prior to May 19, 2000, is considered acceptable for
compliance with the initial test required by paragraph (a) of this
AD.
Note 3: Model 747-400 series airplanes, line numbers 1061 and
subsequent, equipped with GE CF6-80C2 engines, had a third locking
system installed during production in accordance with PRR 80452-102,
and were not modified in accordance with Boeing Service Bulletin
747-78-2151 (which is a retrofit action for airplanes having line
numbers 700 through 1060 inclusive).
Terminating Action
(b) Accomplishment of the functional test of the CDU cone brake,
as specified in paragraph (a) of this AD, constitutes terminating
action for the repetitive tests of the CDU cone brake required by
paragraph (b)(1) of AD 94-15-05.
Corrective Action
(c) If any functional test required by paragraph (a) of this AD
cannot be successfully performed as specified in the referenced
service bulletin, or if any discrepancy is detected during any
functional test required by paragraph (a) of this AD, accomplish
either paragraph (c)(1) or (c)(2) of this AD.
(1) Prior to further flight, repair in accordance with Boeing
Service Bulletin 747-78A2166, Revision 1, dated October 9, 1997;
Boeing Alert Service Bulletin 747-78A2166, Revision 2, dated March
15, 2001; Boeing Service Bulletin 747-78A2113, Revision 2, dated
June 8, 1995; or Revision 3, dated September 11, 1997. After the
effective date of this AD, only Boeing Alert Service Bulletin 747-
78A2166, Revision 2; or Boeing Service Bulletin 747-78A2113,
Revision 2 or Revision 3; may be used.
(2) The airplane may be operated in accordance with the
provisions and limitations specified in the operator's FAA-approved
Minimum Equipment List, provided that no more than one thrust
reverser on the airplane is inoperative.
New Requirements of This AD
Installation of Thrust Reverser Actuator System Lock and Associated
Actions
(d) For airplanes listed in Boeing Service Bulletin 747-78-2151,
Revision 2, dated January 13, 2000: Within 36 months after the
effective date of this AD, do paragraphs (d)(1) and (d)(2) of this
AD.
(1) Install and activate a thrust reverser actuator system
(TRAS) lock on each thrust reverser per the Accomplishment
Instructions of Boeing Service Bulletin 747-78-2151, Revision 1,
dated August 21, 1997; as revised by Notice of Status Change (NSC)
747-78-2151 NSC 04, dated November 26, 1997; and NSC 747-78-2151 NSC
05, dated December 18, 1997; or Boeing Service Bulletin 747-78-2151,
Revision 2, dated January 13, 2000. The procedures for completing
the installation and activating the TRAS lock include replacing a
certain microswitch pack with a new one; adding new wires; routing
certain new wire bundles; changing certain wiring, circuit breakers,
and components; installing thrust-reverser relay panels; and
performing a functional test to ensure that the thrust reverser
actuation system operates properly.
(2) Prior to or concurrently with the installation required by
paragraph (d)(1) of this AD, do the requirements of paragraphs
(d)(2)(i), (d)(2)(ii), (d)(2)(iii), (d)(2)(iv), and (d)(2)(v) of
this AD.
(i) Install a bracket and fastening hardware for the third
locking system on each thrust reverser, per Lockheed Martin Service
Bulletin 78-1007, Revision 1, dated March 18, 1997; or Middle River
Aircraft Systems Service Bulletin 78-1007, Revision 2, dated March
10, 1998.
(ii) Install wiring provisions in various areas of the airplane,
per the Accomplishment Instructions of Boeing Service Bulletin 747-
78-2132, Revision 2, dated December 11, 1997.
(iii) Install a TRAS lock (also called an electromechanical lock
or brake) and a flexible drive cable on each thrust reverser, per
Lockheed Martin Service Bulletin 78-1020, Revision 2, dated March
20, 1997; or Middle River Aircraft Systems Service Bulletin 78-1020,
Revision 3, dated March 16, 1998; or Middle River Aircraft Systems
CF6-80C2B Service Bulletin 78-1020, Revision 4, dated October 10,
2002.
(iv) Install new integrated display system (IDS) software in six
integrated display units and three electronic flight information/
engine indication and crew alerting system (EICAS) interface units,
per the Accomplishment Instructions of Boeing Service Bulletin 747-
31-2242, dated April 18, 1996. Where the service bulletin specifies
installation of IDS software version 995-0017-012, installation of
IDS software version 995-0017-013, 995-0017-014, 995-0017-015, 995-
0017-016, 995-0017-018, 3174-COL-EG5-01, 3177-COL-EG5-02, or 3176-
COL-EG5-03 is also acceptable for compliance with this paragraph.
(v) Replace two central maintenance computers (CMC), part number
622-8592-103, with new, improved CMCs, part number 622-8592-105, and
install new software for the CMCs, per the Accomplishment
Instructions of Boeing Service Bulletin 747-45-2016, Revision 1,
dated May 2, 1996. Where the service bulletin specifies installation
of CMC software version 685-2270-009, installation of CMC software
version 685-2270-010, or 685-2270-011 is also acceptable for
compliance with this paragraph.
Repetitive Tests
(e) For airplanes on which a TRAS lock is installed on the
thrust reversers: Within 1,000 flight hours after the installation
of the TRAS lock, or within 90 flight hours after the effective date
of this AD, whichever is later, do a functional test of the TRAS
lock (also called an electromechanical lock or brake) per the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
78A2166, Revision 2, dated March 15, 2001. Then, repeat this test at
least every 1,000 flight hours. If the functional test cannot be
successfully performed, before further flight, repair per the
Accomplishment Instructions of the service bulletin, and repeat the
test until it is successful.
[[Page 51442]]
Dispatch Limitations
(f) If, prior to accomplishment of Boeing Service Bulletin 747-
78-2151 on any airplane, it becomes necessary to install a thrust
reverser with the TRAS lock installed, dispatch of the airplane is
allowed per the provisions and limitations specified in the 747-400
Master Minimum Equipment List (MMEL), provided that the thrust
reverser assembly that has the TRAS lock installed is deactivated
per the 747-400 Dispatch Deviations Guide, Boeing Document D6U10151,
dated June 28, 2002. Installation of a thrust reverser without a
TRAS lock installed and reactivation of the thrust reverser must be
accomplished within the time constraints specified in the MMEL.
(g) If, after accomplishment of Boeing Service Bulletin 747-78-
2151 on any airplane, it becomes necessary to install a thrust
reverser assembly that does not have the TRAS lock installed,
dispatch of the airplane is allowed per the provisions and
limitations specified in the Boeing Model 747-400 MMEL, provided
that the thrust reverser assembly that does not have the TRAS lock
installed is deactivated per the 747-400 Dispatch Deviations Guide,
Boeing Document D6U10151, dated June 28, 2002. Installation of a
thrust reverser with the TRAS lock installed and reactivation of the
thrust reverser must be accomplished within the time constraints
specified in the MMEL.
Alternative Methods of Compliance
(h)(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, Seattle Aircraft Certification
Office (ACO), FAA. Operators shall submit their requests through an
appropriate FAA Principal Maintenance Inspector, who may add
comments and then send it to the Manager, Seattle ACO.
(2) Alternative methods of compliance, approved previously in
accordance with AD 2000-09-03, amendment 39-11711, are not
considered to be approved as alternative methods of compliance with
this AD.
Note 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Seattle ACO.
Special Flight Permits
(i) 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.
Incorporation by Reference
(j) Unless otherwise provided by this AD, the actions shall be
done in accordance with the service bulletins listed in Table 1 of
this AD, as applicable:
Table 1.--Applicable Service Bulletins
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Service bulletin Revision Date
----------------------------------------------------------------------------------------------------------------
Boeing Service Bulletin 747-31-2242.... original........................... April 18, 1996.
Boeing Service Bulletin 747-45-2016.... 1.................................. May 2, 1996.
Boeing Service Bulletin 747-78-2132.... 2.................................. December 11, 1997.
Boeing Service Bulletin 747-78-2151, as 1.................................. August 21, 1997.
revised by.
Notice of Status Change 747-78-2151 NSC NSC 04............................. November 26, 1997.
04 and.
Notice of Status Change 747-78-2151 NSC NSC 05............................. December 18, 1997 .
05.
Boeing Service Bulletin 747-78-2151.... 2.................................. January 13, 2000.
Boeing Service Bulletin 747-78A2113.... 2.................................. June 8, 1995.
Boeing Service Bulletin 747-78A2113.... 3.................................. September 11, 1997.
Boeing Service Bulletin 747-78A2166.... 1.................................. October 9, 1997.
Boeing Alert Service Bulletin 747- 2.................................. March 15, 2001.
78A2166.
Lockheed Martin Service Bulletin 78- 1.................................. March 18, 1997.
1007.
Middle River Aircraft Systems Service 2.................................. March 10, 1998.
Bulletin 78-1007.
Lockheed Martin Service Bulletin 78- 2.................................. March 20, 1997.
1020.
Middle River Aircraft Systems Service 3.................................. March 16, 1998.
Bulletin 78-1020.
Middle River Aircraft Systems CF6-80C2B 4.................................. October 10, 2002.
Service Bulletin 78-1020.
----------------------------------------------------------------------------------------------------------------
Middle River Aircraft Systems CF6-80C2B Service Bulletin 78-1020,
Revision 4, dated October 10, 2002, contains the following list of
effective pages:
------------------------------------------------------------------------
Revision
Page No. level shown Date shown on page
on page
------------------------------------------------------------------------
1, 7, 20....................... 4 October 10, 2002.
2-6, 8-19, 21-37............... 3 March 16, 1998.
------------------------------------------------------------------------
(1) The incorporation by reference of the service bulletins in
Table 2 of this AD is approved by the Director of the Federal
Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Table
2 follows:
Table 2.--Service Bulletins Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Service bulletin Revision Date
----------------------------------------------------------------------------------------------------------------
Boeing Service Bulletin 747-31-2242.... original........................... April 18, 1996.
Boeing Service Bulletin 747-45-2016.... 1.................................. May 2, 1996.
Boeing Service Bulletin 747-78-2132.... 2.................................. December 11, 1997.
Boeing Service Bulletin 747-78-2151, as 1.................................. August 21, 1997.
revised by.
[[Page 51443]]
Notice of Status Change 747-78-2151 NSC NSC 04............................. November 26, 1997.
04 and.
Notice of Status Change 747-78-2151 NSC NSC 05............................. December 18, 1997.
05.
Boeing Service Bulletin 747-78-2151.... 2.................................. January 13, 2000.
Boeing Alert Service Bulletin 747- 2.................................. March 15, 2001.
78A2166.
Middle River Aircraft Systems CF6-80C2B 4.................................. October 10, 2002.
Service Bulletin 78-1020.
----------------------------------------------------------------------------------------------------------------
(2) The incorporation by reference of the service bulletins in
Table 3 of this AD was approved previously by the Director of the
Federal Register as of September 6, 2000 (65 FR 47252, August 2,
2000). Table 3 follows:
Table 3.--Service Bulletins Previously Incorporated by Reference
------------------------------------------------------------------------
Service bulletin Revision Date
------------------------------------------------------------------------
Lockheed Martin Service 1 March 18, 1997.
Bulletin 78-1007.
Middle River Aircraft Systems 2 March 10, 1998.
Service Bulletin 78-1007.
Lockheed Martin Service 2 March 20, 1997.
Bulletin 78-1020.
Middle River Aircraft Systems 3 March 16, 1998.
Service Bulletin 78-1020.
------------------------------------------------------------------------
(3) The incorporation by reference of Boeing Service Bulletin
747-78A2113, Revision 2, dated June 8, 1995; and Boeing Service
Bulletin 747-78A2113, Revision 3, dated September 11, 1997; was
approved previously by the Director of the Federal Register as of
March 13, 2000 (65 FR 5742, February 7, 2000).
(4) The incorporation by reference of Boeing Service Bulletin
747-78A2166, Revision 1, dated October 9, 1997; was approved
previously by the Director of the Federal Register as of August 25,
1999 (64 FR 39003, July 21, 1999).
(5) Copies may be obtained from Boeing Commercial Airplane
Group, P.O. Box 3707, Seattle, Washington 98124-2207; and
Distribution, Lockheed Martin Technical Services, 1330 Kemper Meadow
Drive, suite 110-C, Cincinnati, Ohio 45240. 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.
Effective Date
(k) This amendment becomes effective on October 1, 2003.
Appendix 1--Thrust Reverser CDU Cone Brake Test
1. This procedure contains steps to do a check of the holding
torque of the CDU cone brake.
2. CDU cone brake check (Figure 1):
A. Prepare to do the check:
(1) Open the fan cowl panels.
(2) Pull up on the manual release handle to unlock the electro-
mechanical brake.
(3) Pull the manual brake release lever on the CDU to release
the cone brake.
Note: This will release the pre-load tension that may occur
during a stow cycle.
(4) Return the manual brake release lever to the locked position
to engage the cone brake.
(5) Remove the two bolts that hold the lockout plate to the CDU
and remove the lockout plate.
(6) Install a \1/4\-inch drive and a dial-type torque wrench
into the CDU drive pad.
Caution: Do not use more than 100 pound-inches of torque when
you do this check. Excessive torque will damage the CDU.
(7) Turn the torque wrench to try to manually extend the
translating cowl until you get at least 15 pound-inches.
Note: The cone brake prevents movement in the extend direction
only. If you try to measure the holding torque in the retract
direction, you will get a false reading.
(8) If the torque is less than 15 pound-inches, you must replace
the CDU.
(9) Reinstall the lockout plate.
B. Return the airplane to its usual condition:
(1) Fully retract the thrust reverser (unless already
accomplished).
(2) Pull down on the manual release handle on the electro-
mechanical brake until the handle fully engages the retaining clip
(unless already accomplished).
Note: This will lock the electro-mechanical brake.
(3) Close the fan cowl panels.
BILLING CODE 4910-13-P
[[Page 51444]]
[GRAPHIC] [TIFF OMITTED] TR27AU03.002
[[Page 51445]]
Issued in Renton, Washington, on August 13, 2003.
Neil D. Schalekamp,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-21151 Filed 8-26-03; 8:45 am]
BILLING CODE 4910-13-C