Airworthiness Directives; Boeing Model 767-200, -300, and -300F Series Airplanes, 5917-5920 [05-1805]
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Federal Register / Vol. 70, No. 23 / Friday, February 4, 2005 / Rules and Regulations
List of Subjects in 7 CFR Part 905
Grapefruit, Marketing agreements,
Oranges, Reporting and recordkeeping
requirements, Tangelos, Tangerines.
For the reasons discussed in the
preamble, 7 CFR Part 905 is amended as
follows:
I
PART 905—ORANGES, GRAPEFRUIT,
TANGERINES, AND TANGELOS
GROWN IN FLORIDA
1. The authority citation for part 905
continues to read as follows:
I
Authority: 7 U.S.C. 601–674.
§ 905.350
[Removed and reserved]
2. Section 905.350 is removed and
reserved.
I
Dated: January 31, 2005.
Kenneth C. Clayton,
Acting Administrator, Agricultural Marketing
Service.
[FR Doc. 05–2154 Filed 2–3–05; 8:45 am]
BILLING CODE 3410–02–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19201; Directorate
Identifier 2003–NM–100–AD; Amendment
39–13959; AD 2005–03–03]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 767–200, –300, and –300F Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to all Boeing Model 767–
200, –300, and –300F series airplanes.
That AD currently requires examination
of maintenance records to determine if
Titanine JC5A (also known as Desoto
823E508) corrosion inhibiting
compound (‘‘C.I.C.’’) was ever used;
inspection for cracks or corrosion and
corrective action, if applicable;
repetitive inspections and C.I.C.
applications; and modification of the aft
trunnion area of the outer cylinder,
which terminates the need for the
repetitive inspections and C.I.C.
applications. This new AD also requires,
for certain other airplanes, repetitive
inspections for cracks or corrosion,
corrective action if necessary, and
repetitive C.I.C. applications. This AD is
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prompted by a report that JC5A was
used on more airplanes during
production than previously identified.
We are issuing this AD to prevent severe
corrosion in the main landing gear
(MLG) outer cylinder at the aft trunnion,
which could develop into stress
corrosion cracking and consequent
collapse of the MLG.
DATES: This AD becomes effective
March 11, 2005.
The incorporation by reference of a
certain publication listed in the AD is
approved by the Director of the Federal
Register as of March 11, 2005.
On May 6, 2002 (67 FR 19322, April
19, 2002), the Director of the Federal
Register approved the incorporation by
reference of a certain other publication.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207. You
can examine this information 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: https://www.archives.gov/
federal_register/
code_of_federal_regulations/
ibr_locations.html.
Docket: The AD docket contains the
proposed AD, comments, and any final
disposition. You can examine the AD
docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the U.S. Department of Transportation,
400 Seventh Street, SW., room PL–401,
Washington, DC. This docket number is
FAA–2004–19201; the directorate
identifier for this docket is 2003–NM–
100–AD.
FOR FURTHER INFORMATION CONTACT:
Suzanne Masterson, Aerospace
Engineer, Airframe Branch, ANM–120S,
FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
Washington 98055–4056; telephone
(425) 917–6441; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend part 39 of the
Federal Aviation Regulations (14 CFR
part 39) with an AD to supersede AD
2002–08–07, amendment 39–12715, (67
FR 19322, April 19, 2002). The existing
AD applies to all Boeing Model 767–
200, –300, and –00F series airplanes.
The proposed AD was published in the
Federal Register on September 29, 2004
(69 FR 58103). That action proposed to
continue to require examination of
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5917
maintenance records to determine if
Titanine JC5A (also known as Desoto
823E508) corrosion inhibiting
compound (‘‘C.I.C.’’) was ever used;
inspection for cracks or corrosion and
corrective action, if applicable;
repetitive inspections and C.I.C.
applications; and modification of the aft
trunnion area of the outer cylinder,
which terminates the need for the
repetitive inspections and C.I.C.
applications. The action also proposed
to require, for certain other airplanes,
repetitive inspections for cracks or
corrosion, corrective action if necessary,
and repetitive C.I.C. applications.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been submitted on the proposed AD.
Support for the Proposed AD
One commenter supports the
proposed AD.
Request To Add Compliance Statement
One commenter requests that we add
the verbiage, ‘‘required as indicated,
unless accomplished previously,’’ to the
compliance section of the proposed AD.
The commenter believes this statement
is needed to obtain credit for the
inspections and repetitive C.I.C
applications it accomplished, prior to
issuance of the proposed AD, on its
airplanes in accordance with Boeing
Alert Service Bulletin 767–32A0192,
Revision 1, dated March 13, 2003.
We partially agree, since similar
language to that suggested by the
commenter is found in paragraph (e) of
this AD. As part of our effort to use
plain language in ADs, we have
rewritten the compliance statement as
follows: ‘‘You are responsible for having
the actions required by this AD
performed within the compliance times
specified, unless the actions have
already been done.’’ While the language
has changed, the intent of the statement
is the same. Therefore, no further
change to this AD is necessary in this
regard.
Request To Add Credit for Previous
Accomplishment
One commenter requests that we add
a note to the proposed AD, which would
give credit for work accomplished in
compliance with AD 2002–08–07. The
commenter suggests the following note,
or language similar to this:
‘‘Accomplishment of the actions
required by paragraph[s] (a) through (l)
of AD 2002–08–07 amendment 39–
12715, is acceptable for compliance
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with the requirements of paragraph[s]
(g) through (r) of this AD. This AD does
not require that those actions be
repeated.’’ We infer that the commenter
believes the proposed AD, as written,
would require repeating work the
commenter has already accomplished.
We do not agree that a credit note is
necessary because paragraph (e) of this
AD, as discussed in the first comment,
already gives credit for any work
previously accomplished. Operators
should note that the new requirements
of paragraph (s) of this AD are
applicable only to Boeing Model 767–
200, –300, and –300F series airplanes,
with line numbers (L/Ns) 834 through
874 inclusive. Furthermore, if an
operator previously accomplished these
new required actions on any applicable
airplane (L/Ns 834 through 874
inclusive), then that airplane is also in
compliance, as stated in paragraph (e) of
this AD. Therefore no change to this AD
is necessary in this regard.
Explanation of Change to This AD
Boeing has received a Delegation
Option Authorization (DOA). We have
revised this final rule to delegate the
authority to approve an alternative
method of compliance for any repair
required by this AD to the Authorized
Representative for the Boeing DOA
Organization rather than the Designated
Engineering Representative (DER).
Conclusion
We have carefully reviewed the
available data, including the comments
that have been submitted, and
determined that air safety and the
public interest require adopting the AD
with the change described previously.
We have determined that these changes
will neither increase the economic
burden on any operator nor increase the
scope of the AD.
Costs of Compliance
There are about 848 airplanes of the
affected design in the worldwide fleet.
This AD will affect about 357 airplanes
of U.S. registry. The new requirements
of this AD add no additional economic
burden for operators affected by AD
2002–08–07. The current costs for this
AD are repeated for the convenience of
affected operators, as follows:
ESTIMATED COSTS
Work
hours
Action
Average labor
rate per hour
Parts
Cost per airplane
$65, per application
cycle.
130 ...........................
$23,205 per application cycle.
390 ...........................
130, per inspection
cycle.
390 ...........................
10,516 ......................
139,230.
46,410, per inspection cycle.
C.I.C. Application ........................................
1
$65
None ........
Cross Bolt Hole Inspection—Bushings Removed.
Restoration for Bushings Removed ............
Cross Bolt Inner Chamfer Inspection—
Bushings Not Removed.
Restoration for Bushings Not Removed .....
Terminating Action ......................................
2
65
None ........
6
2
65
65
None ........
None ........
6
64
65
65
None ........
$6,356 ......
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
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or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD. See the ADDRESSES section for
a location to examine the regulatory
evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Fleet cost
46,410.
139,230.
3,754,212.
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing amendment 39–12715 (67 FR
19322, April 19, 2002), and by adding the
following new airworthiness directive
(AD):
I
2005–03–03 Boeing: Amendment 39–13959.
Docket No. FAA–2004–19201;
Directorate Identifier 2003–NM–100–AD.
Effective Date
(a) This AD becomes effective March 11,
2005.
Affected ADs
(b) This AD supersedes AD 2002–08–07,
amendment 39–12715 (67 FR 19322, April
19, 2002).
Adoption of the Amendment
Applicability
(c) This AD applies to all Boeing Model
767–200, –300, and –300F series airplanes,
certificated in any category.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
Unsafe Condition
(d) This AD was prompted by a report that
Titanine JC5A (also known as Desoto
823E508) was used on more airplanes during
I
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production than previously identified. We
are issuing this AD to prevent severe
corrosion in the main landing gear (MLG)
outer cylinder at the aft trunnion, which
could develop into stress corrosion cracking
and consequent collapse of the MLG.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Requirements of AD 2002–08–07,
Amendment 39–12715
Line Numbers (L/N) 1 Through 833 Inclusive,
and 875 and Subsequent
(f) For airplanes with L/Ns 1 through 833
inclusive, and 875 and subsequent: Do the
actions specified in paragraphs (g) through
(q) of this AD, as applicable.
Records Examination
(g) Within 90 days after May 6, 2002 (the
effective date of AD 2002–08–07, amendment
39–12715), examine airplane records to
determine if Titanine JC5A or Desoto
823E508 (hereafter collectively referred to as
‘‘JC5A’’) corrosion inhibiting compound
(‘‘C.I.C.’’) was used in the aft trunnion area
of the MLG outer cylinder during general
maintenance, overhaul, or incorporation of
Boeing Alert Service Bulletin 767–32A0148,
dated December 21, 1995, Revision 1, dated
October 10, 1996 (required by paragraph (e)
of AD 96–21–06, amendment 39–9783), or
Revision 2, dated November 30, 2000; in
accordance with Boeing Alert Service
Bulletin 767–32A0192, dated May 31, 2001;
or Revision 1, dated March 13, 2003. If
records do not show conclusively which
compound was used, assume JC5A was used.
Refer to Boeing Alert Service Bulletin 767–
32A0192, dated May 31, 2001, for the line
numbers of airplanes that were assembled
new using JC5A.
Note 1: Prior to January 31, 2001, if BMS
3–27 was ordered from Boeing, Boeing
shipped JC5A as a substitute.
MLGs on Which JC5A Was Not Used
(h) Except as provided by paragraph (p)
(‘‘Use of JC5A Prohibited’’) of this AD, if,
according to the criteria of paragraph (g) of
this AD, JC5A was never used, no further
action is required by this AD.
C.I.C. Applications, Inspections, and
Corrective Actions if Necessary
(i) For Category 1 MLG outer cylinders as
identified in Boeing Alert Service Bulletin
767–32A0192, dated May 31, 2001: If,
according to the criteria of paragraph (g) of
this AD, JC5A may have been used, perform
the actions specified in both paragraphs (j)
and (k) of this AD, as applicable, in
accordance with Boeing Alert Service
Bulletin 767–32A0192, dated May 31, 2001;
or Revision 1, dated March 13, 2003.
(j) For MLGs and MLG outer cylinders
identified in paragraphs (j)(1), (j)(2), and (j)(3)
of this AD: Within 90 days after May 6, 2002,
perform the C.I.C. application on the MLG in
accordance with ‘‘Part 3—C.I.C. Application’’
of the Accomplishment Instructions of
Boeing Alert Service Bulletin 767–32A0192,
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dated May 31, 2001; or Revision 1, dated
March 13, 2003. Thereafter, repeat at
intervals not to exceed 180 days until the
terminating action required by paragraph (q)
of this AD has been accomplished.
(1) MLG outer cylinders that are less than
3 years old since new.
(2) MLGs that have been overhauled less
than 3 years before May 6, 2002.
(3) MLGs on which rework per Boeing
Alert Service Bulletin 767–32A0148, dated
December 21, 1995; Revision 1, dated
October 10, 1996; or Revision 2, dated
November 30, 2000, was accomplished less
than 3 years before May 6, 2002.
(k) Before the MLG outer cylinder is 3
years old since new, since last overhaul, or
since rework per Boeing Alert Service
Bulletin 767–32A0148, dated December 21,
1995; Revision 1, dated October 10, 1996; or
Revision 2, dated November 30, 2000; or
within 90 days after May 6, 2002; whichever
is later; perform a detailed inspection for
cracks and corrosion of the cross bolt bushing
holes and chamfers in accordance with ‘‘Part
1—Cross Bolt Hole Inspection—Bushings
Removed’’ of the Accomplishment
Instructions of Boeing Alert Service Bulletin
767–32A0192, dated May 31, 2001; or
Revision 1, dated March 13, 2003.
Note 2: For the purposes of this AD, a
detailed inspection is defined as: ‘‘An
intensive examination of a specific item,
installation, or assembly to detect damage,
failure, or irregularity. Available lighting is
normally supplemented with a direct source
of good lighting at an intensity deemed
appropriate. Inspection aids such as mirror,
magnifying lenses, etc., may be necessary.
Surface cleaning and elaborate procedures
may be required.’’
(1) If no crack or corrosion is found during
the detailed inspection required by paragraph
(k) of this AD, perform the actions in
paragraphs (k)(1)(i), (k)(1)(ii), and (k)(1)(iii) of
this AD, at the applicable times indicated.
(i) Before further flight, perform the
restoration steps shown in Figure 2 of the
service bulletin; and thereafter at intervals
not to exceed 180 days, perform the C.I.C.
application on the landing gear in accordance
with ‘‘Part 3—C.I.C. Application’’ of the
Accomplishment Instructions of the service
bulletin.
(ii) Within 18 months after performing the
detailed inspection required by paragraph (k)
of this AD, and thereafter at intervals not to
exceed 18 months, perform the detailed
inspection for cracks and corrosion of the
cross bolt hole inner chamfer, in accordance
with ‘‘Part 2—Cross Bolt Hole Inner Chamfer
Inspection—Bushings Not Removed’’ of the
Accomplishment Instructions of the service
bulletin, until the terminating action required
by paragraph (q) of this AD has been
accomplished.
(iii) Before the MLG cylinder is 61⁄2 years
old since new, since last overhaul, or since
rework per Boeing Alert Service Bulletin
767–32A0148, dated December 21, 1995;
Revision 1, dated October 10, 1996; or
Revision 2, dated November 30, 2000;
whichever is later; perform the terminating
action described in paragraph (q) of this AD.
(2) If any corrosion is found on the cross
bolt holes or outer chamfers during the
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5919
detailed inspection required by paragraph (k)
of this AD, before further flight, remove the
corrosion per Figure 2 of the service bulletin.
(i) If all of the corrosion can be removed:
Before further flight, perform the restoration
steps shown in Figure 2 of the service
bulletin; thereafter at intervals not to exceed
180 days, perform the C.I.C. application on
the MLG in accordance with ‘‘Part 3—C.I.C.
Application’’ of the Accomplishment
Instructions of the service bulletin; and
perform the terminating action described in
paragraph (q) of this AD, at the applicable
time specified in paragraph (k)(2)(i)(A) or
(k)(2)(i)(B) of this AD.
(A) If the MLG outer cylinder is less than
5 years old since new, if the MLG was last
overhauled less than 5 years before May 6,
2002, or if rework per Boeing Alert Service
Bulletin 767–32A0148, dated December 21,
1995; Revision 1, dated October 10, 1996; or
Revision 2, dated November 30, 2000; was
accomplished less than 5 years before May 6,
2002: Within 18 months after performing the
detailed inspection required by paragraph (k)
of this AD.
(B) If the MLG outer cylinder is 5 years old
or more since new, if the MLG was last
overhauled 5 years or more before May 6,
2002, or if rework per Boeing Alert Service
Bulletin 767–32A0148, dated December 21,
1995; Revision 1, dated October 10, 1996; or
Revision 2, dated November 30, 2000; was
accomplished 5 years or more before May 6,
2002: Before the MLG outer cylinder is 61⁄2
years old since new, since last overhaul, or
since rework per Boeing Alert Service
Bulletin 767–32A0148, dated December 21,
1995; Revision 1, dated October 10, 1996; or
Revision 2, dated November 30, 2000;
whichever is later.
(ii) If any corrosion cannot be removed,
before further flight, perform the terminating
action described in paragraph (q) of this AD.
(3) If any crack is found anywhere during
the detailed inspection required in paragraph
(k) of this AD, or if corrosion in the inner
cross bolt hole chamfers is found, before
further flight, perform the terminating action
described in paragraph (q) of this AD.
(l) For Category 2 MLG outer cylinders as
identified in Boeing Alert Service Bulletin
767–32A0192, dated May 31, 2001: If,
according to the criteria of paragraph (g) of
this AD, JC5A may have been used, perform
the actions specified in both paragraphs (m)
and (n) of this AD, as applicable, in
accordance with Boeing Alert Service
Bulletin 767–32A0192, dated May 31, 2001;
or Revision 1, dated March 13, 2003.
(m) For MLGs and MLG outer cylinders
identified in paragraphs (m)(1) and (m)(2) of
this AD: Within 90 days after May 6, 2002,
perform the C.I.C. application on the MLG in
accordance with ‘‘Part 3—C.I.C. Application’’
of the Accomplishment Instructions of
Boeing Alert Service Bulletin 767–32A0192,
dated May 31, 2001; or Revision 1, dated
March 13, 2003. Thereafter, repeat the
application at intervals not to exceed 180
days until the terminating action required by
paragraph (q) of this AD has been
accomplished.
(1) MLG outer cylinders that are less than
3 years old since new.
(2) MLGs that have been overhauled less
than 3 years before May 6, 2002.
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(n) Before the MLG outer cylinder is 3
years old since new or since the last
overhaul, or within 90 days after May 6,
2002, whichever is later, perform a detailed
inspection for cracks and corrosion of the
cross bolt hole inner chamfer, in accordance
with ‘‘Part 2—Cross Bolt Hole Inner Chamfer
Inspection—Bushings Not Removed’’ of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 767–32A0192, dated May
31, 2001; or Revision 1, dated March 13,
2003.
(1) If no crack or corrosion is found during
the inspection required by paragraph (n) of
this AD, before further flight, and thereafter
at intervals not to exceed 180 days, perform
the C.I.C. application on the MLG in
accordance with ‘‘Part 3—C.I.C. Application’’
of the Accomplishment Instructions of the
service bulletin, until the next MLG
overhaul. After the next MLG overhaul has
been completed, no further action is required
by this AD.
(2) If any corrosion is found during the
detailed inspection required by paragraph (n)
of this AD, before further flight, remove the
cross bolt bushings and perform the detailed
inspection specified in paragraph (k) of this
AD, and remove the corrosion per Figure 2
of the service bulletin.
(i) If all of the corrosion can be removed,
perform the actions specified in paragraph
(n)(2)(i)(A) and (n)(2)(i)(B) of this AD, at the
applicable times indicated.
(A) Prior to further flight, perform the
restoration steps shown in Figure 2 of the
service bulletin; and thereafter at intervals
not to exceed 180 days, perform the C.I.C.
application on the MLG in accordance with
‘‘Part 3—C.I.C. Application’’ of the
Accomplishment Instructions of the service
bulletin.
(B) Within 18 months after the corrosion
removal required by paragraph (n)(2) of this
AD, perform the terminating action described
in paragraph (q) of this AD.
(ii) If all the corrosion cannot be removed,
before further flight, perform the terminating
action required by paragraph (q) of this AD.
(3) If any crack is found during the detailed
inspection required by paragraph (n) of this
AD, before further flight, perform the
terminating action described in paragraph (q)
of this AD.
Parts Installation
(o) As of May 6, 2002, no person shall
install on any airplane an MLG outer
cylinder unless maintenance records
conclusively show that JC5A has never been
used on that MLG outer cylinder, or unless
it complies with paragraph (q) of this AD.
Use of JC5A Prohibited
(p) As of May 6, 2002, no person shall use
the C.I.C. JC5A in the aft trunnion area of the
MLG outer cylinder on any airplane.
Terminating Action
(q) Perform the terminating action
(including removal of the existing bushings,
repair of the aft trunnion area of the outer
cylinder, and machining and installation of
new bushings) in accordance with ‘‘Part 4—
Terminating Action’’ of the Accomplishment
Instructions of Boeing Alert Service Bulletin
767–32A0192, dated May 31, 2001; or
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Jkt 205001
Revision 1, dated March 13, 2003.
Completion of the terminating action
terminates the requirements for the repetitive
inspections and C.I.C. applications of this
AD.
Credit for Terminating Action
(r) For all airplanes, accomplishment of the
actions specified in paragraph (q) of this AD
is considered acceptable for compliance with
the requirements of paragraph (e) of AD
2002–01–13, amendment 39–12607.
New Requirements of This AD
L/Ns 834 Through 874 Inclusive
(s) For airplanes with L/Ns 834 through
874 inclusive: Do the actions specified in
paragraphs (s)(1), (s)(2), and (s)(3) of this AD.
(1) Within 90 days after the effective date
of this AD, and thereafter at intervals not to
exceed 180 days: Do the actions specified in
paragraph (m) of this AD until the
terminating action required by paragraph (q)
of this AD has been accomplished.
(2) Before the MLG outer cylinder is 3
years old since new or since last overhaul, or
within 90 days after the effective date of this
AD, whichever is later: Do the actions as
specified in paragraph (n) of this AD.
(3) As of the effective date of this AD, the
actions specified in paragraphs (o) and (p) of
this AD must be complied with.
Reporting Requirement
(t) Although the service bulletins
referenced in this AD specify to submit
certain information to the manufacturer, this
AD does not include such a requirement.
Alternative Methods of Compliance (AMOCs)
(u)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Delegation Option Authorization
Organization who has been authorized by the
Manager, Seattle ACO, to make those
findings. For a repair method to be approved,
the repair must meet the certification basis of
the airplane, and the approval must
specifically refer to this AD.
Material Incorporated by Reference
(v) Unless otherwise specified by this AD,
the actions shall be done in accordance with
Boeing Alert Service Bulletin 767–32A0192,
dated May 31, 2001; or Boeing Alert Service
Bulletin 767–32A0192, Revision 1, dated
March 13, 2003.
(1) The Director of the Federal Register
approves the incorporation by reference of
Boeing Alert Service Bulletin 767–32A0192,
Revision 1, dated March 13, 2003 in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) The Director of the Federal Register
previously approved the incorporation by
reference of Boeing Alert Service Bulletin
767–32A0192, dated May 31, 2001, as of May
6, 2002 (67 FR 19322, April 19, 2002).
(3) For copies of the service information,
contact Boeing Commercial Airplanes, P.O.
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
Box 3707, Seattle, Washington 98124–2207.
For information on the availability of this
material at the National Archives and
Records Administration (NARA), call (202)
741–6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html. You may view the AD
docket at the Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street SW., room PL–401, Nassif
Building, Washington, DC.
Issued in Renton, Washington, on January
21, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–1805 Filed 2–3–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20250; Directorate
Identifier 2003–NM–267–AD; Amendment
39–13961; AD 2005–03–05]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model MD–90–30 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is revising an
existing airworthiness directive (AD),
which applies to certain McDonnell
Douglas Model MD–90–30 airplanes.
This AD requires a one-time general
visual inspection to detect wire chafing
damage and to determine adequate
clearance between the disconnect panel
structure and the wires above the aft left
lavatory; and corrective actions, if
necessary. This new AD revises the
applicability of the existing AD. This
AD is prompted by the determination
that certain airplanes unaffected by the
existing AD are subject to the unsafe
condition, and certain other airplanes
should be removed from the
applicability. We are issuing this AD to
prevent damage to certain wires due to
contact between the wires and the
adjacent structure, which could result in
electrical arcing and consequent smoke
and fire in the cabin.
DATES: Effective February 22, 2005.
The incorporation by reference of a
certain publication listed in the AD is
approved by the Director of the Federal
Register as of February 22, 2005.
We must receive comments on this
AD by April 5, 2005.
E:\FR\FM\04FER1.SGM
04FER1
]]>Agencies
[Federal Register Volume 70, Number 23 (Friday, February 4, 2005)]
[Rules and Regulations]
[Pages 5917-5920]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-1805]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19201; Directorate Identifier 2003-NM-100-AD;
Amendment 39-13959; AD 2005-03-03]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 767-200, -300, and -300F
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to all Boeing Model 767-200, -300, and -300F series
airplanes. That AD currently requires examination of maintenance
records to determine if Titanine JC5A (also known as Desoto 823E508)
corrosion inhibiting compound (``C.I.C.'') was ever used; inspection
for cracks or corrosion and corrective action, if applicable;
repetitive inspections and C.I.C. applications; and modification of the
aft trunnion area of the outer cylinder, which terminates the need for
the repetitive inspections and C.I.C. applications. This new AD also
requires, for certain other airplanes, repetitive inspections for
cracks or corrosion, corrective action if necessary, and repetitive
C.I.C. applications. This AD is prompted by a report that JC5A was used
on more airplanes during production than previously identified. We are
issuing this AD to prevent severe corrosion in the main landing gear
(MLG) outer cylinder at the aft trunnion, which could develop into
stress corrosion cracking and consequent collapse of the MLG.
DATES: This AD becomes effective March 11, 2005.
The incorporation by reference of a certain publication listed in
the AD is approved by the Director of the Federal Register as of March
11, 2005.
On May 6, 2002 (67 FR 19322, April 19, 2002), the Director of the
Federal Register approved the incorporation by reference of a certain
other publication.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207. You can examine this information 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: https://
www.archives.gov/federal_register/code_of_federal_regulations/ibr_
locations.html.
Docket: The AD docket contains the proposed AD, comments, and any
final disposition. You can examine the AD docket on the Internet at
https://dms.dot.gov, or in person at the Docket Management Facility
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the U.S.
Department of Transportation, 400 Seventh Street, SW., room PL-401,
Washington, DC. This docket number is FAA-2004-19201; the directorate
identifier for this docket is 2003-NM-100-AD.
FOR FURTHER INFORMATION CONTACT: Suzanne Masterson, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6441; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend part 39 of the
Federal Aviation Regulations (14 CFR part 39) with an AD to supersede
AD 2002-08-07, amendment 39-12715, (67 FR 19322, April 19, 2002). The
existing AD applies to all Boeing Model 767-200, -300, and -00F series
airplanes. The proposed AD was published in the Federal Register on
September 29, 2004 (69 FR 58103). That action proposed to continue to
require examination of maintenance records to determine if Titanine
JC5A (also known as Desoto 823E508) corrosion inhibiting compound
(``C.I.C.'') was ever used; inspection for cracks or corrosion and
corrective action, if applicable; repetitive inspections and C.I.C.
applications; and modification of the aft trunnion area of the outer
cylinder, which terminates the need for the repetitive inspections and
C.I.C. applications. The action also proposed to require, for certain
other airplanes, repetitive inspections for cracks or corrosion,
corrective action if necessary, and repetitive C.I.C. applications.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
submitted on the proposed AD.
Support for the Proposed AD
One commenter supports the proposed AD.
Request To Add Compliance Statement
One commenter requests that we add the verbiage, ``required as
indicated, unless accomplished previously,'' to the compliance section
of the proposed AD. The commenter believes this statement is needed to
obtain credit for the inspections and repetitive C.I.C applications it
accomplished, prior to issuance of the proposed AD, on its airplanes in
accordance with Boeing Alert Service Bulletin 767-32A0192, Revision 1,
dated March 13, 2003.
We partially agree, since similar language to that suggested by the
commenter is found in paragraph (e) of this AD. As part of our effort
to use plain language in ADs, we have rewritten the compliance
statement as follows: ``You are responsible for having the actions
required by this AD performed within the compliance times specified,
unless the actions have already been done.'' While the language has
changed, the intent of the statement is the same. Therefore, no further
change to this AD is necessary in this regard.
Request To Add Credit for Previous Accomplishment
One commenter requests that we add a note to the proposed AD, which
would give credit for work accomplished in compliance with AD 2002-08-
07. The commenter suggests the following note, or language similar to
this: ``Accomplishment of the actions required by paragraph[s] (a)
through (l) of AD 2002-08-07 amendment 39-12715, is acceptable for
compliance
[[Page 5918]]
with the requirements of paragraph[s] (g) through (r) of this AD. This
AD does not require that those actions be repeated.'' We infer that the
commenter believes the proposed AD, as written, would require repeating
work the commenter has already accomplished.
We do not agree that a credit note is necessary because paragraph
(e) of this AD, as discussed in the first comment, already gives credit
for any work previously accomplished. Operators should note that the
new requirements of paragraph (s) of this AD are applicable only to
Boeing Model 767-200, -300, and -300F series airplanes, with line
numbers (L/Ns) 834 through 874 inclusive. Furthermore, if an operator
previously accomplished these new required actions on any applicable
airplane (L/Ns 834 through 874 inclusive), then that airplane is also
in compliance, as stated in paragraph (e) of this AD. Therefore no
change to this AD is necessary in this regard.
Explanation of Change to This AD
Boeing has received a Delegation Option Authorization (DOA). We
have revised this final rule to delegate the authority to approve an
alternative method of compliance for any repair required by this AD to
the Authorized Representative for the Boeing DOA Organization rather
than the Designated Engineering Representative (DER).
Conclusion
We have carefully reviewed the available data, including the
comments that have been submitted, and determined that air safety and
the public interest require adopting the AD with the change described
previously. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
There are about 848 airplanes of the affected design in the
worldwide fleet. This AD will affect about 357 airplanes of U.S.
registry. The new requirements of this AD add no additional economic
burden for operators affected by AD 2002-08-07. The current costs for
this AD are repeated for the convenience of affected operators, as
follows:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Work Average labor
Action hours rate per hour Parts Cost per airplane Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
C.I.C. Application................ 1 $65 None............... $65, per application $23,205 per application cycle.
cycle.
Cross Bolt Hole Inspection-- 2 65 None............... 130.................. 46,410.
Bushings Removed.
Restoration for Bushings Removed.. 6 65 None............... 390.................. 139,230.
Cross Bolt Inner Chamfer 2 65 None............... 130, per inspection 46,410, per inspection cycle.
Inspection--Bushings Not Removed. cycle.
Restoration for Bushings Not 6 65 None............... 390.................. 139,230.
Removed.
Terminating Action................ 64 65 $6,356............. 10,516............... 3,754,212.
--------------------------------------------------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD 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.
For the reasons discussed above, I certify that this AD:
(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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD. See the ADDRESSES section for a location to
examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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. The FAA amends Sec. 39.13 by removing amendment 39-12715 (67 FR
19322, April 19, 2002), and by adding the following new airworthiness
directive (AD):
2005-03-03 Boeing: Amendment 39-13959. Docket No. FAA-2004-19201;
Directorate Identifier 2003-NM-100-AD.
Effective Date
(a) This AD becomes effective March 11, 2005.
Affected ADs
(b) This AD supersedes AD 2002-08-07, amendment 39-12715 (67 FR
19322, April 19, 2002).
Applicability
(c) This AD applies to all Boeing Model 767-200, -300, and -300F
series airplanes, certificated in any category.
Unsafe Condition
(d) This AD was prompted by a report that Titanine JC5A (also
known as Desoto 823E508) was used on more airplanes during
[[Page 5919]]
production than previously identified. We are issuing this AD to
prevent severe corrosion in the main landing gear (MLG) outer
cylinder at the aft trunnion, which could develop into stress
corrosion cracking and consequent collapse of the MLG.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Requirements of AD 2002-08-07, Amendment 39-12715
Line Numbers (L/N) 1 Through 833 Inclusive, and 875 and Subsequent
(f) For airplanes with L/Ns 1 through 833 inclusive, and 875 and
subsequent: Do the actions specified in paragraphs (g) through (q)
of this AD, as applicable.
Records Examination
(g) Within 90 days after May 6, 2002 (the effective date of AD
2002-08-07, amendment 39-12715), examine airplane records to
determine if Titanine JC5A or Desoto 823E508 (hereafter collectively
referred to as ``JC5A'') corrosion inhibiting compound (``C.I.C.'')
was used in the aft trunnion area of the MLG outer cylinder during
general maintenance, overhaul, or incorporation of Boeing Alert
Service Bulletin 767-32A0148, dated December 21, 1995, Revision 1,
dated October 10, 1996 (required by paragraph (e) of AD 96-21-06,
amendment 39-9783), or Revision 2, dated November 30, 2000; in
accordance with Boeing Alert Service Bulletin 767-32A0192, dated May
31, 2001; or Revision 1, dated March 13, 2003. If records do not
show conclusively which compound was used, assume JC5A was used.
Refer to Boeing Alert Service Bulletin 767-32A0192, dated May 31,
2001, for the line numbers of airplanes that were assembled new
using JC5A.
Note 1: Prior to January 31, 2001, if BMS 3-27 was ordered from
Boeing, Boeing shipped JC5A as a substitute.
MLGs on Which JC5A Was Not Used
(h) Except as provided by paragraph (p) (``Use of JC5A
Prohibited'') of this AD, if, according to the criteria of paragraph
(g) of this AD, JC5A was never used, no further action is required
by this AD.
C.I.C. Applications, Inspections, and Corrective Actions if
Necessary
(i) For Category 1 MLG outer cylinders as identified in Boeing
Alert Service Bulletin 767-32A0192, dated May 31, 2001: If,
according to the criteria of paragraph (g) of this AD, JC5A may have
been used, perform the actions specified in both paragraphs (j) and
(k) of this AD, as applicable, in accordance with Boeing Alert
Service Bulletin 767-32A0192, dated May 31, 2001; or Revision 1,
dated March 13, 2003.
(j) For MLGs and MLG outer cylinders identified in paragraphs
(j)(1), (j)(2), and (j)(3) of this AD: Within 90 days after May 6,
2002, perform the C.I.C. application on the MLG in accordance with
``Part 3--C.I.C. Application'' of the Accomplishment Instructions of
Boeing Alert Service Bulletin 767-32A0192, dated May 31, 2001; or
Revision 1, dated March 13, 2003. Thereafter, repeat at intervals
not to exceed 180 days until the terminating action required by
paragraph (q) of this AD has been accomplished.
(1) MLG outer cylinders that are less than 3 years old since
new.
(2) MLGs that have been overhauled less than 3 years before May
6, 2002.
(3) MLGs on which rework per Boeing Alert Service Bulletin 767-
32A0148, dated December 21, 1995; Revision 1, dated October 10,
1996; or Revision 2, dated November 30, 2000, was accomplished less
than 3 years before May 6, 2002.
(k) Before the MLG outer cylinder is 3 years old since new,
since last overhaul, or since rework per Boeing Alert Service
Bulletin 767-32A0148, dated December 21, 1995; Revision 1, dated
October 10, 1996; or Revision 2, dated November 30, 2000; or within
90 days after May 6, 2002; whichever is later; perform a detailed
inspection for cracks and corrosion of the cross bolt bushing holes
and chamfers in accordance with ``Part 1--Cross Bolt Hole
Inspection--Bushings Removed'' of the Accomplishment Instructions of
Boeing Alert Service Bulletin 767-32A0192, dated May 31, 2001; or
Revision 1, dated March 13, 2003.
Note 2: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive examination of a specific item,
installation, or assembly to detect damage, failure, or
irregularity. Available lighting is normally supplemented with a
direct source of good lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying lenses, etc., may be
necessary. Surface cleaning and elaborate procedures may be
required.''
(1) If no crack or corrosion is found during the detailed
inspection required by paragraph (k) of this AD, perform the actions
in paragraphs (k)(1)(i), (k)(1)(ii), and (k)(1)(iii) of this AD, at
the applicable times indicated.
(i) Before further flight, perform the restoration steps shown
in Figure 2 of the service bulletin; and thereafter at intervals not
to exceed 180 days, perform the C.I.C. application on the landing
gear in accordance with ``Part 3--C.I.C. Application'' of the
Accomplishment Instructions of the service bulletin.
(ii) Within 18 months after performing the detailed inspection
required by paragraph (k) of this AD, and thereafter at intervals
not to exceed 18 months, perform the detailed inspection for cracks
and corrosion of the cross bolt hole inner chamfer, in accordance
with ``Part 2--Cross Bolt Hole Inner Chamfer Inspection--Bushings
Not Removed'' of the Accomplishment Instructions of the service
bulletin, until the terminating action required by paragraph (q) of
this AD has been accomplished.
(iii) Before the MLG cylinder is 6\1/2\ years old since new,
since last overhaul, or since rework per Boeing Alert Service
Bulletin 767-32A0148, dated December 21, 1995; Revision 1, dated
October 10, 1996; or Revision 2, dated November 30, 2000; whichever
is later; perform the terminating action described in paragraph (q)
of this AD.
(2) If any corrosion is found on the cross bolt holes or outer
chamfers during the detailed inspection required by paragraph (k) of
this AD, before further flight, remove the corrosion per Figure 2 of
the service bulletin.
(i) If all of the corrosion can be removed: Before further
flight, perform the restoration steps shown in Figure 2 of the
service bulletin; thereafter at intervals not to exceed 180 days,
perform the C.I.C. application on the MLG in accordance with ``Part
3--C.I.C. Application'' of the Accomplishment Instructions of the
service bulletin; and perform the terminating action described in
paragraph (q) of this AD, at the applicable time specified in
paragraph (k)(2)(i)(A) or (k)(2)(i)(B) of this AD.
(A) If the MLG outer cylinder is less than 5 years old since
new, if the MLG was last overhauled less than 5 years before May 6,
2002, or if rework per Boeing Alert Service Bulletin 767-32A0148,
dated December 21, 1995; Revision 1, dated October 10, 1996; or
Revision 2, dated November 30, 2000; was accomplished less than 5
years before May 6, 2002: Within 18 months after performing the
detailed inspection required by paragraph (k) of this AD.
(B) If the MLG outer cylinder is 5 years old or more since new,
if the MLG was last overhauled 5 years or more before May 6, 2002,
or if rework per Boeing Alert Service Bulletin 767-32A0148, dated
December 21, 1995; Revision 1, dated October 10, 1996; or Revision
2, dated November 30, 2000; was accomplished 5 years or more before
May 6, 2002: Before the MLG outer cylinder is 6\1/2\ years old since
new, since last overhaul, or since rework per Boeing Alert Service
Bulletin 767-32A0148, dated December 21, 1995; Revision 1, dated
October 10, 1996; or Revision 2, dated November 30, 2000; whichever
is later.
(ii) If any corrosion cannot be removed, before further flight,
perform the terminating action described in paragraph (q) of this
AD.
(3) If any crack is found anywhere during the detailed
inspection required in paragraph (k) of this AD, or if corrosion in
the inner cross bolt hole chamfers is found, before further flight,
perform the terminating action described in paragraph (q) of this
AD.
(l) For Category 2 MLG outer cylinders as identified in Boeing
Alert Service Bulletin 767-32A0192, dated May 31, 2001: If,
according to the criteria of paragraph (g) of this AD, JC5A may have
been used, perform the actions specified in both paragraphs (m) and
(n) of this AD, as applicable, in accordance with Boeing Alert
Service Bulletin 767-32A0192, dated May 31, 2001; or Revision 1,
dated March 13, 2003.
(m) For MLGs and MLG outer cylinders identified in paragraphs
(m)(1) and (m)(2) of this AD: Within 90 days after May 6, 2002,
perform the C.I.C. application on the MLG in accordance with ``Part
3--C.I.C. Application'' of the Accomplishment Instructions of Boeing
Alert Service Bulletin 767-32A0192, dated May 31, 2001; or Revision
1, dated March 13, 2003. Thereafter, repeat the application at
intervals not to exceed 180 days until the terminating action
required by paragraph (q) of this AD has been accomplished.
(1) MLG outer cylinders that are less than 3 years old since
new.
(2) MLGs that have been overhauled less than 3 years before May
6, 2002.
[[Page 5920]]
(n) Before the MLG outer cylinder is 3 years old since new or
since the last overhaul, or within 90 days after May 6, 2002,
whichever is later, perform a detailed inspection for cracks and
corrosion of the cross bolt hole inner chamfer, in accordance with
``Part 2--Cross Bolt Hole Inner Chamfer Inspection--Bushings Not
Removed'' of the Accomplishment Instructions of Boeing Alert Service
Bulletin 767-32A0192, dated May 31, 2001; or Revision 1, dated March
13, 2003.
(1) If no crack or corrosion is found during the inspection
required by paragraph (n) of this AD, before further flight, and
thereafter at intervals not to exceed 180 days, perform the C.I.C.
application on the MLG in accordance with ``Part 3--C.I.C.
Application'' of the Accomplishment Instructions of the service
bulletin, until the next MLG overhaul. After the next MLG overhaul
has been completed, no further action is required by this AD.
(2) If any corrosion is found during the detailed inspection
required by paragraph (n) of this AD, before further flight, remove
the cross bolt bushings and perform the detailed inspection
specified in paragraph (k) of this AD, and remove the corrosion per
Figure 2 of the service bulletin.
(i) If all of the corrosion can be removed, perform the actions
specified in paragraph (n)(2)(i)(A) and (n)(2)(i)(B) of this AD, at
the applicable times indicated.
(A) Prior to further flight, perform the restoration steps shown
in Figure 2 of the service bulletin; and thereafter at intervals not
to exceed 180 days, perform the C.I.C. application on the MLG in
accordance with ``Part 3--C.I.C. Application'' of the Accomplishment
Instructions of the service bulletin.
(B) Within 18 months after the corrosion removal required by
paragraph (n)(2) of this AD, perform the terminating action
described in paragraph (q) of this AD.
(ii) If all the corrosion cannot be removed, before further
flight, perform the terminating action required by paragraph (q) of
this AD.
(3) If any crack is found during the detailed inspection
required by paragraph (n) of this AD, before further flight, perform
the terminating action described in paragraph (q) of this AD.
Parts Installation
(o) As of May 6, 2002, no person shall install on any airplane
an MLG outer cylinder unless maintenance records conclusively show
that JC5A has never been used on that MLG outer cylinder, or unless
it complies with paragraph (q) of this AD.
Use of JC5A Prohibited
(p) As of May 6, 2002, no person shall use the C.I.C. JC5A in
the aft trunnion area of the MLG outer cylinder on any airplane.
Terminating Action
(q) Perform the terminating action (including removal of the
existing bushings, repair of the aft trunnion area of the outer
cylinder, and machining and installation of new bushings) in
accordance with ``Part 4--Terminating Action'' of the Accomplishment
Instructions of Boeing Alert Service Bulletin 767-32A0192, dated May
31, 2001; or Revision 1, dated March 13, 2003. Completion of the
terminating action terminates the requirements for the repetitive
inspections and C.I.C. applications of this AD.
Credit for Terminating Action
(r) For all airplanes, accomplishment of the actions specified
in paragraph (q) of this AD is considered acceptable for compliance
with the requirements of paragraph (e) of AD 2002-01-13, amendment
39-12607.
New Requirements of This AD
L/Ns 834 Through 874 Inclusive
(s) For airplanes with L/Ns 834 through 874 inclusive: Do the
actions specified in paragraphs (s)(1), (s)(2), and (s)(3) of this
AD.
(1) Within 90 days after the effective date of this AD, and
thereafter at intervals not to exceed 180 days: Do the actions
specified in paragraph (m) of this AD until the terminating action
required by paragraph (q) of this AD has been accomplished.
(2) Before the MLG outer cylinder is 3 years old since new or
since last overhaul, or within 90 days after the effective date of
this AD, whichever is later: Do the actions as specified in
paragraph (n) of this AD.
(3) As of the effective date of this AD, the actions specified
in paragraphs (o) and (p) of this AD must be complied with.
Reporting Requirement
(t) Although the service bulletins referenced in this AD specify
to submit certain information to the manufacturer, this AD does not
include such a requirement.
Alternative Methods of Compliance (AMOCs)
(u)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(2) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Delegation Option
Authorization Organization who has been authorized by the Manager,
Seattle ACO, to make those findings. For a repair method to be
approved, the repair must meet the certification basis of the
airplane, and the approval must specifically refer to this AD.
Material Incorporated by Reference
(v) Unless otherwise specified by this AD, the actions shall be
done in accordance with Boeing Alert Service Bulletin 767-32A0192,
dated May 31, 2001; or Boeing Alert Service Bulletin 767-32A0192,
Revision 1, dated March 13, 2003.
(1) The Director of the Federal Register approves the
incorporation by reference of Boeing Alert Service Bulletin 767-
32A0192, Revision 1, dated March 13, 2003 in accordance with 5
U.S.C. 552(a) and 1 CFR part 51.
(2) The Director of the Federal Register previously approved the
incorporation by reference of Boeing Alert Service Bulletin 767-
32A0192, dated May 31, 2001, as of May 6, 2002 (67 FR 19322, April
19, 2002).
(3) For copies of the service information, contact Boeing
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
For information on the availability of this material at the National
Archives and Records Administration (NARA), call (202) 741-6030, or
go to https://www.archives.gov/federal_register/code_of_federal_
regulations/ibr_locations.html. You may view the AD docket at the
Docket Management Facility, U.S. Department of Transportation, 400
Seventh Street SW., room PL-401, Nassif Building, Washington, DC.
Issued in Renton, Washington, on January 21, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-1805 Filed 2-3-05; 8:45 am]
BILLING CODE 4910-13-P
