[Federal Register Volume 66, Number 164 (Thursday, August 23, 2001)]
[Proposed Rules]
[Pages 44313-44316]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-21225]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-189-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to all Boeing Model 767-200, -300, 
and -300F series airplanes. This proposal would require examination of 
maintenance records to determine if Titanine 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. This action is necessary 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. This action is intended to address the 
identified unsafe condition. The FAA is also planning to issue 
additional rulemaking to exclude the use of Titanine JC5A for 
compliance with previously issued ADs.

DATES: Comments must be received by September 24, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-189-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-189-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: John Craycraft, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2782; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
     For each issue, state what specific change to the proposed 
AD is being requested.
     Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-189-AD.'' The postcard will be date stamped 
and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2001-NM-189-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received reports indicating that an approved corrosion 
inhibiting compound (``C.I.C.'') has caused severe corrosion in the 
main landing gear (MLG) at the outer cylinder aft trunnion on Boeing 
Model 767 series airplanes. The corrosion was found on

[[Page 44314]]

landing gear that were previously reworked using the C.I.C. Titanine 
JC5A (hereafter referred to as ``JC5A'') during accomplishment of 
Boeing Alert Service Bulletin 767-32A0148, dated December 21, 1995, or 
Revision 1, dated October 10, 1996 (which were referenced in AD 96-21-
06, amendment 39-9783 (61 FR 55080, October 24, 1996), as the 
appropriate source of service information for accomplishing the 
terminating action). During general maintenance; overhaul; 
accomplishment of Boeing Alert Service Bulletin 767-32A0148, dated 
December 21, 1995, or Revision 1, dated October 10, 1996; or when 
assembled new, JC5A was commonly used as a substitute for C.I.C. BMS 3-
27 (Mastinox 6856K) on aft trunnion components.
    Over time, the JC5A deteriorates and becomes hard and dry. If 
moisture enters the outer cylinder aft trunnion and mixes with JC5A, a 
series of chemical reactions occur and the reaction products degrade 
the primer and cadmium plating. This may lead to corrosion in the aft 
trunnion where the JC5A was used. There is more potential for corrosion 
in aft trunnions with an undercut on the inner diameter of the aft 
trunnion in the area of the bushing, which serves as a lubrication 
reservoir, which certain airplanes had as delivered. The presence of 
JC5A on the aft trunnion, if not corrected, could result in severe 
corrosion in the MLG outer cylinder at the aft trunnion, which could 
develop into stress corrosion cracking and consequent collapse of the 
MLG.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
767-32A0192, dated May 31, 2001. The service bulletin describes 
procedures for examination of airplane records to determine if JC5A 
C.I.C. was ever used; application of a different C.I.C.; inspections 
for cracks or corrosion of the cross bolt hole inner chamfer and cross 
bolt bushing holes and chamfers; and corrective and follow-on actions, 
if necessary. Corrective and follow-on actions include corrosion 
repair; 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. Accomplishment of the actions specified in the service 
bulletin is intended to adequately address the identified unsafe 
condition.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require accomplishment of the actions specified in 
the service bulletin described previously.

Cost Impact

    There are approximately 806 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 489 airplanes of U.S. registry 
would be affected by this proposed AD. The approximate work hours 
required to accomplish the proposed actions are indicated in the table 
below. It is estimated that the average labor rate is $60 per work 
hour. Cost of required parts per airplane and the estimated cost impact 
of the proposed AD on U.S. operators is indicated in the table below.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                    Total fleet
         Category             Labor costs  (at $60 per          Parts costs       Total cost per    cost  (489
                                        hour)                                        airplane       airplanes)
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1.........................  Inspection--Bushings          [Reserved]............          $1,500        $733,500
                             Removed--25 hours/$1,500.
1.........................  Inspection--Bushings Not      [Reserved]............           1,200         586,800
                             Removed--20 hours/$1,200.
1.........................  C.I.C. Application--5 hours/  [Reserved]............             300         146,700
                             $300.
1.........................  Terminating Action--218       $6,356................          19,436       9,504,204
                             hours/$13,080.
2.........................  Inspection--Bushings Not      [Reserved]............           1,200         586,800
                             Removed--20 hours/$1,200.
2.........................  C.I.C. Application--5 hours/  [Reserved]............             300         146,700
                             $300.
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 Category 1: Airplanes with an undercut in the aft trunnion bore.
 Category 2: Airplanes without an undercut in the aft trunnion bore.

    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the proposed requirements 
of this AD action, and that no operator would accomplish those actions 
in the future if this proposed 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 proposed herein 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. Therefore, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this 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) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
part 39 of the Federal Aviation Regulations (14 CFR part 39) as 
follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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

[[Page 44315]]

Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

Boeing: Docket 2001-NM-189-AD.

    Applicability: All Model 767-200, -300, and -300F series 
airplanes, 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 (m) 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 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, accomplish 
the following:

Records Examination

    (a) Within 90 days after the effective date of this AD, examine 
airplane records to determine if Titanine JC5A (hereafter 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, or Revision 1, dated 
October 10, 1996 (required by paragraph (e) of AD 96-21-06, 
amendment 39-9783), in accordance with Boeing Alert Service Bulletin 
767-32A0192, dated May 31, 2001. 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 which were assembled new using JC5A.

    Note 2: 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

    (b) Except as provided by paragraph (1) of this AD, if, 
according to the criteria of paragraph (a) 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

    (c) 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 (a) of this AD, JC5A may have 
been used, perform the actions specified in both paragraphs (d) and 
(e) of this AD, as applicable, in accordance with Boeing Alert 
Service Bulletin 767-32A0192, dated May 31, 2001.
    (d) For MLGs and MLG outer cylinders identified in paragraphs 
(d)(1), (d)(2), and (d)(3) of this AD: Within 90 days after the 
effective date of this AD, 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. Thereafter, repeat at intervals not to 
exceed 180 days until the terminating action required by paragraph 
(i) 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 ago.
    (3) MLGs on which rework per Boeing Alert Service Bulletin 767-
32A0148, dated December 21, 1995, or Revision 1, dated October 10, 
1996, was accomplished less than 3 years ago.
    (e) Before the MLG outer cylinder is 3 years old since new; 
since last overhaul; since rework per Boeing Alert Service Bulletin 
767-32A0148, dated December 21, 1995, or Revision 1, dated October 
10, 1996; or within 90 days after the effective date of this AD; 
whichever is later, perform a detailed visual 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.

    Note 3: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

    (1) If no crack or corrosion is found during the detailed visual 
inspection required by paragraph (e) of this AD, perform the actions 
in paragraphs (e)(1)(i), (e)(1)(ii), and (e)(1)(iii) of this AD, at 
the applicable times indicated.
    (i) Before further flight, 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 visual 
inspection required by paragraph (e) of this AD, and thereafter at 
intervals not to exceed 18 months, perform the detailed visual 
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 (i) of this AD has been accomplished.
    (iii) Before the MLG cylinder is 6\1/2\years since new; since 
last overhaul; or since rework per Boeing Alert Service Bulletin 
767-32A0148, dated December 21, 1995, or Revision 1, dated October 
10, 1996; whichever is later, perform the terminating action 
described in paragraph (i) of this AD.
    (2) If any corrosion is found on the cross bolt holes or outer 
chamfers during the detailed visual inspection required by paragraph 
(e) 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, 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, and perform the terminating action described in 
paragraph (i) of this AD, at the applicable time specified in 
paragraphs (e)(2)(i)(A) or (e)(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 ago; or, if 
rework per Boeing Alert Service Bulletin 767-32A0148, dated December 
21, 1995, or Revision 1, dated October 10, 1996, was accomplished 
less than 5 years ago: Within 18 months after performing the 
detailed visual inspection required by paragraph (e) 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 ago or more; or, if rework 
per Boeing Alert Service Bulletin 767-32A0148, dated December 21, 
1995, or Revision 1, dated October 10, 1996, was accomplished 5 
years ago or more: 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, or Revision 
1, dated October 10, 1996; whichever is later.
    (ii) If corrosion cannot be removed, before further flight, 
perform the terminating action described in paragraph (i) of this 
AD.
    (3) If any crack is found anywhere during the detailed visual 
inspection required in paragraph (e) 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 (i) of this 
AD.
    (f) 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 (a) of this AD, JC5A may have 
been used, perform the actions specified in both paragraphs (g) and 
(h) of this AD, as applicable, in accordance with Boeing Alert 
Service Bulletin 767-32A0192, dated May 31, 2001.
    (g) For MLGs and MLG outer cylinders identified in paragraphs 
(g)(1) and (g)(2) of this AD: Within 90 days after the effective 
date of this AD, 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. Thereafter, repeat the application at intervals not to 
exceed 180 days until the terminating action required by paragraph 
(i) 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 ago.
    (h) Before the MLG outer cylinder is 3 years old since new or 
since the last

[[Page 44316]]

overhaul, or within 90 days of the effective date of this AD, 
whichever is later, perform a detailed visual inspection for cracks 
and corrosion of the cross bolt hole inner chamfer, in accordance 
with ``Part 2--Crossbolt Hole Inner Chamfer Inspection--Bushings Not 
Removed'' of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 767-32A0192, dated May 31, 2001.
    (1) If no crack or corrosion is found during the inspection 
required by paragraph (h) 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 visual 
inspection required by paragraph (h) of this AD, prior to further 
flight, remove the cross bolt bushings and perform the detailed 
visual inspection specified in paragraph (e) 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 (h)(2)(i)(A) and (h)(2)(i)(B) of this AD, at 
the applicable times indicated.
    (A) Prior to 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.
    (B) Within 18 months after the corrosion removal required by 
paragraph (h)(2) of this AD, perform the terminating action 
described in paragraph (i) of this AD.
    (ii) If all the corrosion cannot be removed, before further 
flight, perform the terminating action required by paragraph (i) of 
this AD.
    (3) If any crack is found during the detailed visual inspection 
required by paragraph (h) of this AD, before further flight, perform 
the terminating action described in paragraph (i) of this AD.

Terminating Action

    (i) 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. Completion of the terminating action terminates the 
requirements for the repetitive inspection and C.I.C. applications 
of this AD.
    (j) Accomplishment of the actions specified in paragraph (i) of 
this AD is considered acceptable for compliance with the 
requirements of paragraph (e) of AD 96-21-06, amendment 39-9783.

Spares

    (k) As of the effective date of this AD, no person shall install 
on any airplane an MLG outer cylinder unless it complies with either 
paragraph (b) or paragraph (i) of this AD, as applicable.
    (l) As of the effective date of this AD, no person shall use on 
any airplane the corrosion inhibiting compound Titanine JC5A.

Alternative Methods of Compliance

    (m) 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.

    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

    (n) Special flight permits may be issued in accordance with 
Secs. 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.

    Issued in Renton, Washington, on August 16, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-21225 Filed 8-22-01; 8:45 am]
BILLING CODE 4910-13-P