[Federal Register Volume 69, Number 188 (Wednesday, September 29, 2004)]
[Proposed Rules]
[Pages 58103-58107]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-21820]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19201; Directorate Identifier 2003-NM-100-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767-200, -300, and -300F 
Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) for 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 proposed AD 
would also require, for certain other airplanes, repetitive inspections 
for cracks or corrosion, corrective action if necessary, and repetitive 
C.I.C. applications. This proposed AD is prompted by a report that JC5A 
was used on more airplanes during production than previously 
identified. We are proposing 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: We must receive comments on this proposed AD by November 15, 
2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web Site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide Rulemaking Web Site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., room PL-401, on 
the plaza level of the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Technical information: 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.
    Plain language information: Marcia Walters, [email protected].

SUPPLEMENTARY INFORMATION:

Docket Management System (DMS)

    The FAA has implemented new procedures for maintaining AD dockets 
electronically. As of May 17, 2004, new AD actions are posted on DMS 
and assigned a docket number. We track each action and assign a 
corresponding directorate identifier. The DMS AD docket number is in 
the form ``Docket No. FAA-2004-99999.'' The Transport Airplane 
Directorate identifier is in the form ``Directorate Identifier 2004-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier 
(``Old Docket Number'') as a cross-reference for searching purposes.

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2004-19201; 
Directorate Identifier 2003-NM-100-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of our 
docket Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You can review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit http://dms.dot.gov.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve

[[Page 58104]]

the clarity of our communications that affect you. You can get more 
information about plain language at http://www.faa.gov/language and 
http://www.plainlanguage.gov.

Examining the Docket

    You can examine the AD docket on the Internet at http://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 DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the DMS receives them.

Discussion

    On April 11, 2002, we issued AD 2002-08-07, amendment 39-12715 (67 
FR 19322, April 19, 2002), for all Boeing Model 767-200, -300, and -
300F series airplanes. That AD requires examination of maintenance 
records to determine if Titanine JC5A (also known as Desoto 823E508, 
and hereafter collectively referred to as JC5A) 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. That AD was prompted by reports of an approved 
C.I.C. causing severe corrosion in the MLG at the outer cylinder aft 
trunnion on Boeing Model 767 series airplanes. We issued that AD to 
prevent severe corrosion in the MLG outer cylinder at the aft trunnion, 
which could develop into stress corrosion cracking and consequent 
collapse of the MLG.

Actions Since Existing AD Was Issued

    Since we issued AD 2002-08-07, we have determined that the 
identified unsafe condition (i.e., corrosion in the aft trunnion caused 
by the use of JC5A, a C.I.C. that deteriorates over time and degrades 
primer and cadmium plating when it comes into contact with moisture) 
addressed in that AD could still exist on 15 Model 767-200, -300, and -
300F series airplanes of U.S. registry (within the group of line 
numbers (L/N) 834 through 874 inclusive). We have been advised that 
JC5A was used on more airplanes during production than those previously 
identified in the original issue of Boeing Alert Service Bulletin 767-
32A0192. Based on previous information and the records examination 
required by AD 2002-08-07, an operator could have incorrectly 
determined that JC5A had not been used on certain airplanes and 
consequently not corrected the unsafe condition. Therefore, we have 
determined that these airplanes are subject to the inspections, C.I.C 
applications, and modification required by AD 2002-08-07.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 767-32A0192, 
Revision 1, dated March 13, 2003. The procedures specified in Revision 
1 of the service bulletin are essentially the same as the procedures 
specified in the original issue of the service bulletin, as cited in AD 
2002-08-07. Revision 1 of the service bulletin identifies affected 
airplanes, L/Ns 834 through 874, as assembled new with JC5A in the 
outer cylinder aft trunnion. Accomplishing the actions specified in the 
service information is intended to adequately address the unsafe 
condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. Therefore, we are proposing this AD, which 
would supersede AD 2002-08-07. This proposed AD would continue to 
require, for certain airplanes, examination of maintenance records to 
determine if JC5A 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 proposed AD would also 
require, for certain other airplanes, repetitive inspections for cracks 
or corrosion, corrective action if necessary, and repetitive C.I.C. 
applications. This proposed AD would require you to use the service 
information described previously to perform these actions except as 
discussed under ``Differences Between the Proposed AD and the Service 
Bulletins.''

Differences Between the Proposed AD and the Service Bulletins

    Operators should note that, although the Accomplishment 
Instructions of the referenced service bulletins require reporting all 
corrosion found in the aft trunnions of certain airplanes, this 
proposed AD would not require that action.

Change to Existing AD

    This proposed AD would retain all requirements of AD 2002-08-07. 
Since AD 2002-08-07 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                             Corresponding  requirement
       Requirement in AD 2002-08-07             in this  proposed AD
------------------------------------------------------------------------
Paragraph (a).............................  Paragraph (g).
Paragraph (b).............................  Paragraph (h).
Paragraph (c).............................  Paragraph (i).
Paragraph (d).............................  Paragraph (j).
Paragraph (e).............................  Paragraph (k).
Paragraph (f).............................  Paragraph (l).
Paragraph (g).............................  Paragraph (m).
Paragraph (h).............................  Paragraph (n).
Paragraph (i).............................  Paragraph (q).
Paragraph (j).............................  Paragraph (r).
Paragraph (k).............................  Paragraph (o).
Paragraph (l).............................  Paragraph (p).
------------------------------------------------------------------------

    We have also changed all references to the ambiguous time of 
``years ago'' in paragraphs (j)(2), (j)(3), (k)(2)(i)(A), (k)(2)(i)(B), 
and (m)(2) of this proposed AD to ``years before May 6, 2002.''

Costs of Compliance

    There are about 848 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 357 airplanes of 
U.S. registry. The new requirements of this proposed 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
----------------------------------------------------------------------------------------------------------------
                                              Average
              Action                 Work    labor rate     Parts       Cost per airplane        Fleet cost
                                    hours     per hour
----------------------------------------------------------------------------------------------------------------
C.I.C. Application...............        1          $65        (\1\)  $65, per application  $23,205 per
                                                                       cycle.                application cycle.

[[Page 58105]]

 
Cross Bolt Hole Inspection--             2           65        (\1\)  130.................  46,410.
 Bushings Removed.
Restoration for Bushings Removed.        6           65        (\1\)  390.................  139,230.
Cross Bolt Inner Chamfer                 2           65        (\1\)  130, per inspection   46,410, per
 Inspection--Bushings Not Removed.                                     cycle.                inspection cycle.
Restoration for Bushings Not             6           65        (\1\)  390.................  139,230.
 Removed.
Terminating Action...............       64           65        6,356  10,581..............  3,777,417.
----------------------------------------------------------------------------------------------------------------
\1\ None.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. 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 proposed 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, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing amendment 39-12715 (67 FR 
19322, April 19, 2002) and adding the following new airworthiness 
directive (AD):

Boeing: Docket No. FAA-2004-19201; Directorate Identifier 2003-NM-
100-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this airworthiness directive (AD) action by November 15, 2004.

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 
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 39-9783: 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 39-9783), 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

[[Page 58106]]

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.
    (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.

[[Page 58107]]

    (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 a 
Boeing Company Designated Engineering Representative who has been 
authorized by the Manager, Seattle ACO, to make those findings. For 
a repair method to be approved, the approval must specifically refer 
to this AD.

    Issued in Renton, Washington, on September 20, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-21820 Filed 9-28-04; 8:45 am]
BILLING CODE 4910-13-P