[Federal Register Volume 71, Number 22 (Thursday, February 2, 2006)]
[Proposed Rules]
[Pages 5623-5626]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-1419]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23762; Directorate Identifier 2005-NM-226-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for all Boeing Model 767 airplanes. This proposed AD would require 
repetitive inspections for cracking in the skin, the bulkhead outer 
chord, and the strap of the bulkhead outer chord at station (STA) 
1725.5; and repair if necessary. This proposed AD also provides for 
repairs, which are optional for airplanes on which no cracking is 
found, that terminate certain inspections. This proposed AD results 
from reports of cracking in the skin panel common to stringer 7R and 
aft of the STA 1725.5 butt splice, and in the strap of the bulkhead 
outer chord at STA 1725.5. We are proposing this AD to detect and 
correct cracking in the skin, the bulkhead outer chord, or the strap of 
the bulkhead outer chord in this area, which could progress into 
surrounding areas and result in reduced structural integrity of the 
support structure for the vertical or horizontal stabilizer and 
subsequent loss of control of the airplane.

DATES: We must receive comments on this proposed AD by March 20, 2006.

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.

[[Page 5624]]

    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for the service information identified in this 
proposed AD.

FOR FURTHER INFORMATION CONTACT: Candice Gerretsen, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6428; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

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 in the ADDRESSES section. Include the docket number ``FAA-2006-
23762; Directorate Identifier 2005-NM-226-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 
that 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 may review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.

Examining the Docket

    You may 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 Docket Management System 
receives them.

Discussion

    We have received several reports indicating that cracking has been 
found in the skin panel common to stringer 7R and aft of the station 
(STA) 1725.5 butt splice, and in the bulkhead outer chord strap at STA 
1725.5, on several Boeing Model 767 airplanes. The cracking in the skin 
panel was found on airplanes that had accumulated between 13,342 and 
35,641 total flight cycles. Similar cracking was found during fatigue 
tests of Model 767 airplanes. The cracking in the bulkhead outer chord 
strap originated at a fastener hole above stringer 7R in the same area 
where the skin cracking was found. Cracking in these areas, if not 
corrected, could progress into surrounding areas and result in reduced 
structural integrity of the support structure for the vertical or 
horizontal stabilizer and subsequent loss of control of the airplane.

Relevant Service Information

    We have reviewed Boeing Special Attention Service Bulletin 767-53-
0118, dated September 8, 2005. The service bulletin describes 
procedures for the following repetitive inspections for cracking:
     Part 1: Detailed external inspections of the skin aft of 
STA 1725.5, between stringers 6R and 8R.
     Part 2: Detailed inspections of the bulkhead outer chord 
and the strap of the bulkhead outer chord, and surface high frequency 
eddy current (HFEC) inspections of the strap of the bulkhead outer 
chord at STA 1725.5.
    The service bulletin refers to the structural repair manual (SRM) 
for procedures for repairing any crack found in the skin or the strap 
of the bulkhead outer chord. If cracking is found in the bulkhead outer 
chord, the service bulletin specifies to contact Boeing for repair 
procedures. The service bulletin specifies that repairing per a certain 
procedure in the SRM eliminates the need to continue the Part 1 
inspections. The service bulletin also specifies that repairing per 
certain other procedures in the SRM eliminates the need to continue the 
Part 1 and Part 2 inspections.
    The service bulletin specifies a compliance time of 15,000 total 
flight cycles or 3,000 flight cycles after the original issue date on 
the service bulletin for performing the initial Part 1 and Part 2 
inspections. The service bulletin specifies a repetitive interval not 
to exceed 6,000 flight cycles for the Part 1 and Part 2 inspections. 
Any cracking must be repaired before further flight.
    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 airplanes 
of this same type design. For this reason, we are proposing this AD, 
which would require accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Between the Proposed AD and Service Information.''

Differences Between the Proposed AD and Service Information

    The service bulletin specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions in one of the following ways:
     Using a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by an Authorized Representative 
for the Boeing Commercial Airplanes Delegation Option Authorization 
Organization whom we have authorized to make those findings.
    The service bulletin specifies compliance times relative to the 
date of issuance of the service bulletin; however, this proposed AD 
would require compliance before the specified compliance time after the 
effective date of this AD.
    These differences have been coordinated with Boeing.

Costs of Compliance

    There are about 905 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD.

[[Page 5625]]



                                                 Estimated Costs
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                                                                                  Number of
                                                 Average                            U.S.-
             Action                Work hours   labor rate   Cost per  airplane   registered      Fleet cost
                                                 per hour                         airplanes
----------------------------------------------------------------------------------------------------------------
Part 1 Inspection, per                      5          $65  $325, per                    387  $125,775, per
 inspection cycle.                                           inspection cycle.                 inspection cycle.
Part 2 Inspections, per                     9           65  $585, per                    387  $226,395, per
 inspection cycle.                                           inspection cycle.                 inspection cycle.
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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 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 and placed it in the AD docket. 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Boeing: Docket No. FAA-2006-23762; Directorate Identifier 2005-NM-
226-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by March 20, 
2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Boeing Model 767-200, -300, -300F, 
and -400ER series airplanes, certificated in any category.

Unsafe Condition

    (d) This AD results from reports of cracking in the skin panel 
common to stringer 7R and aft of the station (STA) 1725.5 butt 
splice, and in the strap of the bulkhead outer chord at STA 1725.5. 
We are issuing this AD to detect and correct cracking in the skin, 
the bulkhead outer chord, or the strap of the bulkhead outer chord 
in this area, which could progress into surrounding areas and result 
in reduced structural integrity of the support structure for the 
vertical or horizontal stabilizer and subsequent loss of control of 
the airplane.

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.

Repetitive Inspections

    (f) Perform repetitive detailed and high frequency eddy current 
inspections for cracking in the skin, the bulkhead outer chord, and 
the strap of the bulkhead outer chord at STA 1725.5, in accordance 
with the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 767-53-0118, dated September 8, 2005. Do the 
initial and repetitive Part I and Part 2 inspections at the times 
specified in paragraph 1.E., Compliance, of the service bulletin; 
except, where the service bulletin specifies a compliance time after 
the issuance of the service bulletin, this AD requires compliance 
within the specified compliance time after the effective date of 
this AD.

Repair

    (g) If any cracking is found during any inspection required by 
paragraph (f) of this AD: Before further flight, perform applicable 
repairs in accordance with the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 767-53-0118, dated September 8, 
2005; except, where the service bulletin specifies to contact Boeing 
for repair instructions, before further flight, repair the cracking 
using a method approved in accordance with the procedures specified 
in paragraph (i) of this AD.

Optional Terminating Action

    (h) Completing repairs specified in the Accomplishment 
Instructions of the service bulletin terminates repetitive 
inspections required by paragraph (f) of this AD as specified in 
paragraphs (h)(1) and (h)(2) of this AD.
    (1) Completing repairs specified in paragraph 3.B.3.a. of the 
service bulletin terminates both the Part 1 and Part 2 inspections 
required by paragraph (f) of this AD.
    (2) Completing repairs specified in paragraph 3.B.4.a. of the 
service bulletin terminates the Part 1 inspections required by 
paragraph (f) of this AD. Part 2 inspections must continue as 
required by paragraph (f) of this AD until the repairs specified in 
paragraph 3.B.3.a. of the service bulletin are completed.

Alternative Methods of Compliance (AMOCs)

    (i)(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) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

[[Page 5626]]

    (3) 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 Commercial Airplanes 
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.

    Issued in Renton, Washington, on January 26, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-1419 Filed 2-1-06; 8:45 am]
BILLING CODE 4910-13-P