[Federal Register Volume 67, Number 159 (Friday, August 16, 2002)]
[Proposed Rules]
[Pages 53529-53531]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-20709]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-10-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain Boeing Model 767-
200 and -300 series airplanes, that currently requires repetitive 
inspections to find discrepancies of the barrel nuts that attach the 
vertical fin to body section 48, and follow-on actions. For certain 
airplanes, the existing AD requires replacement of certain bolts with 
new bolts. The existing AD also provides for optional terminating 
actions for the repetitive inspections. This new action would reduce 
the compliance time for the inspections; change the torque 
specification; and mandate eventual replacement of all H-11 steel alloy 
barrel nuts and bolts with Inconel nuts and bolts, which would end the 
repetitive inspections. The actions specified by the proposed AD are 
intended to find and fix corroded, cracked, or broken barrel nuts that 
attach the vertical fin to body section 48, which could result in 
reduced structural integrity of the vertical fin attachment joint, loss 
of the vertical fin, and consequent loss of controllability of the 
airplane. This action is intended to address the identified unsafe 
condition.

DATES: Comments must be received by September 30, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-10-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 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. 2002-NM-10-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 this AD may be obtained from 
Boeing Commercial Airplane Group, PO Box 3707, Seattle, Washington 
98124-2207. This information may be examined at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

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) 227-2772; fax (425) 227-1181.
    Other Information: Sandi Carli, Airworthiness Directive Technical 
Editor/Writer; telephone (425) 687-4243, fax (425) 687-4248. Questions 
or comments may also be sent via the Internet using the following 
address: [email protected]. Questions or comments sent via the 
Internet as attached electronic files must be formatted in Microsoft 
Word 97 for Windows or ASCII text.

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 2002-NM-10-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. 2002-NM-10-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On September 14, 2001, the FAA issued AD 2001-19-04, amendment 39-
12444 (66 FR 48538, September 21, 2001), applicable to certain Boeing 
Model 767-200 and -300 series airplanes, to require repetitive 
inspections to find discrepancies of the barrel nuts that attach the 
vertical fin to body section 48, and follow-on actions. For certain 
airplanes, that action requires replacement of certain bolts with new 
bolts. That action also provides for optional terminating actions for 
the repetitive inspections. The requirements of that AD are necessary 
to find and fix corroded, cracked, or broken barrel nuts that attach 
the vertical fin to body section 48, which could result in reduced 
structural integrity of the vertical fin attachment joint, loss of the 
vertical fin, and consequent loss of controllability of the airplane.

Actions Since Issuance of Previous Rule

    In the preamble to AD 2001-19-04, we specified that the actions 
required by that AD were considered ``interim action'' until final 
action was identified, at which time we may consider further 
rulemaking. We have now determined that it is necessary to mandate the 
optional terminating actions, and this proposed AD follows from that 
determination.

[[Page 53530]]

    Since the issuance of AD 2001-19-04, we have received information 
indicating that the torque specification of 2,000 inch-pounds specified 
in Boeing Service Bulletin 767-53-0085, dated May 14, 1998; and Boeing 
Alert Service Bulletin 767-53A0085, Revision 1, dated July 1, 1999 
(referenced in the existing AD as the sources of service information 
for accomplishment of the actions), is not sufficient to accurately 
detect corrosion of the barrel nuts and bolts. Therefore, the revised 
service information (below) increases the torque specification to 
between 3,700 and 4,100 inch-pounds, and recommends eventual 
replacement of all 16 H-11 steel alloy barrel nuts and bolts that 
attach the vertical fin with Inconel nuts and bolts, for all airplanes.

Explanation of Relevant Service Information

    We have reviewed and approved Boeing Service Bulletin 767-53A0085, 
Revision 2, dated May 2, 2002. The procedures in the service bulletin 
specify reducing the compliance time for the inspections specified in 
the existing service information (above); and modifying all airplanes 
to ensure that H-11 steel alloy barrel nuts and bolts that attach the 
vertical fin to body section 48 are replaced with Inconel nuts and 
bolts (in the existing service information, replacement of the bolts 
was recommended for Group 1 airplanes only). The procedures also 
specify that the torque check is now between 3,700 and 4,100 inch-
pounds applied to each bolt, instead of the 2,000 inch-pounds specified 
in the existing service information. 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 supersede AD 2001-19-04 to continue to require 
repetitive inspections to find discrepancies of the barrel nuts that 
attach the vertical fin to body section 48, and follow-on actions. For 
certain airplanes, the proposed AD would continue to require 
replacement of certain bolts with new bolts. This new action would 
reduce the compliance time for the inspections; change the torque 
specification applied to affected bolts; and mandate the previously 
optional terminating action by eventual replacement of all H-11 steel 
alloy barrel nuts and bolts with Inconel nuts and bolts, which would 
end the repetitive inspections. The actions would be required to be 
accomplished in accordance with the service bulletin described 
previously, except as discussed below.

Explanation of Change Made to Existing Requirements

    We have changed all references to a ``detailed visual inspection'' 
in the existing AD to ``detailed inspection'' in this proposed action.

Cost Impact

    There are approximately 549 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 221 airplanes of U.S. registry 
would be affected by this proposed AD.
    The actions that are currently required by AD 2001-19-04 take 
approximately 2 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the currently required actions on U.S. operators is estimated 
to be $120 per airplane.
    The inspections that are proposed in this AD action would take 
approximately 1 work hour per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the proposed inspections on U.S. operators is estimated to be 
$13,260, or $60 per airplane.
    The replacement that is proposed in this AD action would take 
approximately 8 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts would cost 
approximately $6,528 per airplane. Based on these figures, the cost 
impact of the proposed replacement on U.S. operators is estimated to be 
$1,548,768, or $7,008 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the current or proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted. The cost 
impact figures discussed in AD rulemaking actions represent only the 
time necessary to perform the specific actions actually required by the 
AD. These figures typically do not include incidental costs, such as 
the time required to gain access and close up, planning time, or time 
necessitated by other administrative actions.

Regulatory Impact

    The regulations 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.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-12444 (66 FR 
48538, September 21, 2001), and by adding a new airworthiness directive 
(AD), to read as follows:

Boeing: Docket 2002-NM-10-AD. Supersedes AD 2001-19-04, Amendment 
39-12444.

    Applicability: Model 767-200 and -300 series airplanes, line 
numbers 1 through 574 inclusive, 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 (g)(1) 
of this AD. The request should include an assessment of the effect 
of the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not

[[Page 53531]]

been eliminated, the request should include specific proposed 
actions to address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To find and fix corroded, cracked, or broken barrel nuts that 
attach the vertical fin to body section 48, which could result in 
reduced structural integrity of the vertical fin attachment joint, 
loss of the vertical fin, and consequent loss of controllability of 
the airplane; accomplish the following:

Restatement of Requirements of AD 2001-19-04

Internal/External Detailed Inspections

    (a) Do internal and external detailed inspections of the barrel 
nuts at the 16 locations that attach the vertical fin to body 
section 48 to find discrepancies (i.e., cracked or damaged sealant, 
signs of corrosion damage, cracked or broken barrel nuts). Do the 
inspections at the times specified in paragraphs (a)(1) and (a)(2) 
of this AD, as applicable; per Part 1 of the Accomplishment 
Instructions of Boeing Service Bulletin 767-53-0085, dated May 14, 
1998; or Boeing Alert Service Bulletin 767-53A0085, Revision 1, 
dated July 1, 1999; or Revision 2, dated May 2, 2002.

    Note 2: For the purposes of this AD, a detailed 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) For airplanes on which the inspections specified in 
paragraph (a) of this AD have been done within the last 3 years per 
Boeing 767 Maintenance Planning Document (MPD) D622T001, Items 5380-
311-021 and 5380-312-021: Do the inspections at the later of the 
times specified in paragraphs (a)(1)(i) and (a)(1)(ii) of this AD.
    (i) Within 3 years or 6,000 flight cycles after doing the most 
recent inspection per the MPD, whichever comes first.
    (ii) Within 45 days after October 9, 2001 (the effective date AD 
2001-19-04, amendment 39-12444).
    (2) For airplanes on which the inspections specified in 
paragraph (a) of this AD have NOT been done within the last 3 years 
per Boeing 767 MPD D622T001, Items 5380-311-021 and 5380-312-021: Do 
the inspections within 45 days after October 9, 2001.

Follow-On Actions

    (b) If no discrepancy is found during any inspection specified 
in paragraph (a) of this AD: Before further flight, do a torque 
check of each of the 16 bolts in the barrel nuts that attach the 
vertical fin to body section 48 to determine if any bolt turns, per 
Part 2 of the Accomplishment Instructions of Boeing Service Bulletin 
767-53-0085, dated May 14, 1998; or Boeing Alert Service Bulletin 
767-53A0085, Revision 1, dated July 1, 1999; or Revision 2, dated 
May 2, 2002.
    (1) If no bolt turns: Repeat the inspections required by 
paragraph (a) of this AD (and applicable follow-on actions) every 3 
years or 6,000 flight cycles, whichever comes first; until 
paragraphs (d) and (e) of this AD are done.
    (2) If any bolt turns: Before further flight, do the actions 
specified in paragraphs (b)(2)(i) and (b)(2)(ii) of this AD, as 
applicable. Then repeat the inspections required by paragraph (a) of 
this AD (and applicable follow-on actions) every 3 years or 6,000 
flight cycles, whichever comes first; until paragraphs (d) and (e) 
of this AD are done.
    (i) For all airplanes: Replace the barrel nut at that bolt with 
a new, Inconel barrel nut per Part 3 of the Accomplishment 
Instructions of the service bulletin. No further action is required 
for that barrel nut only.
    (ii) For Group 1 airplanes: If an H-11 steel alloy bolt is 
installed with the affected barrel nut, replace the bolt with a new, 
Inconel bolt per Figure 5 of the Accomplishment Instructions of the 
service bulletin. No further action is required for that bolt only.
    (c) If any discrepancy of any barrel nut is found during any 
inspection specified in paragraph (a) or (d) of this AD: Before 
further flight, do the actions specified in paragraphs (c)(1) and 
(c)(2) of this AD, as applicable.
    (1) For all airplanes: Replace the affected barrel nut with a 
new, Inconel barrel nut per Part 3 of the Accomplishment 
Instructions of Boeing Service Bulletin 767-53-0085, dated May 14, 
1998; or Boeing Alert Service Bulletin 767-53A0085, Revision 1, 
dated July 1, 1999; or Revision 2, dated May 2, 2002. No further 
action is required for that barrel nut only.
    (2) For Group 1 airplanes: If an H-11 steel alloy bolt is 
installed with the affected barrel nut, replace the bolt with a new, 
Inconel bolt per Figure 5 of the Accomplishment Instructions of the 
service bulletin. No further action is required for that bolt only.

New Requirements of this AD

Detailed Inspection/Torque Check

    (d) Within 18 months after doing the initial inspections 
required by paragraph (a) of this AD, or within 90 days after the 
effective date of this AD, whichever is later: Do internal and 
external detailed inspections and a torque check (between 3,700 and 
4,100 inch-pounds of torque) of the barrel nuts at the 16 locations 
that attach the vertical fin to body section 48 to find 
discrepancies (i.e., cracked or damaged sealant, signs of corrosion 
damage, cracked or broken barrel nuts) per Boeing Service Bulletin 
767-53A0085, Revision 2, dated May 2, 2002. Repeat the inspections 
and check after that every 18 months until paragraph (e) of this AD 
is done. As of the effective date of this AD, only Revision 2 of the 
service bulletin may be used.

    Note 3: Accomplishment of the inspections and replacements 
before the effective date of this AD per Boeing Service Bulletin 
767-53-0085, dated May 14, 1998; or Boeing Alert Service Bulletin 
767-53A0085, Revision 1, dated July 1, 1999; is considered 
acceptable for compliance with the applicable actions specified in 
paragraphs (a), (b), and (c) of this AD.

Terminating Action

    (e) Within 36 months after the effective date of this AD: 
Replace all 16 H-11 steel alloy barrel nuts and bolts that attach 
the vertical fin to body section 48, with Inconel barrel nuts and 
bolts, per Boeing Service Bulletin 767-53A0085, Revision 2, dated 
May 2, 2002. Such replacement ends the repetitive inspections 
required by this AD.

Spares

    (f) As of the effective date of this AD: No person shall 
install, on any airplane, an Inconel vertical fin attach bolt, 
unless an Inconel barrel nut is installed at the same location; nor 
shall any person install an H-11 steel alloy attachment nut or bolt 
on the vertical fin on any airplane.

Alternative Methods of Compliance

    (g)(1) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Seattle Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Seattle ACO.
    (2) Alternative methods of compliance, approved previously in 
accordance with AD 2001-19-04, amendment 39-12444, are approved as 
alternative methods of compliance with paragraph (a)(1) of this AD.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (h) 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 9, 2002.
Vi Lipski,
Manager Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-20709 Filed 8-15-02; 8:45 am]
BILLING CODE 4910-13-P