[Federal Register Volume 71, Number 98 (Monday, May 22, 2006)]
[Proposed Rules]
[Pages 29275-29276]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-7740]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24814; Directorate Identifier 2006-NM-093-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 detailed and high frequency eddy current (HFEC) inspections 
of the station (STA) 1809.5 bulkhead for cracking and corrective 
actions if necessary. This proposed AD results from fatigue cracks 
found in the forward outer chord and horizontal inner chord at STA 
1809.5. We are proposing this AD to detect and correct cracking in the 
bulkhead structure at STA 1809.5, which could result in failure of the 
bulkhead structure for carrying the flight loads of the horizontal 
stabilizer, and consequent loss of controllability of the airplane.

DATES: We must receive comments on this proposed AD by July 6, 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.
    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-
24814; Directorate Identifier 2006-NM-093-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 a report indicating that two operators found 
fatigue cracks in the forward outer chord of the station (STA) 1809.5 
airframe bulkhead, on four Boeing Model 767 airplanes. Those airplanes 
had accumulated between 13,942 and 29,588 total flight cycles. Also, 
three operators reported finding cracks in the horizontal inner chord 
between stringer 12L and 12R, on several Boeing Model 767 airplanes. 
Those airplanes had accumulated between 8,448 and 35,991 total flight 
cycles. Cracking in the bulkhead structure at STA 1809.5 could grow and 
lead to failure of the bulkhead structure for carrying the flight loads 
of the horizontal stabilizer. This condition, if not corrected, could 
result in loss of controllability of the airplane.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 767-53A0131, dated 
March 30, 2006. The service bulletin describes procedures for 
accomplishing repetitive detailed and high frequency eddy current 
(HFEC) inspections of the STA 1809.5 bulkhead for cracking and 
corrective actions as applicable. Specifically, those inspections 
include the following:
     Part 1 of the service bulletin specifies doing a detailed 
inspection of the exterior of the skin at STA 1809.5 between stringers 
3L and 10L and detailed and HFEC inspections of the forward outer chord 
and surrounding structure between stringers 3L and 10L.
     Part 2 of the service bulletin specifies doing a detailed 
inspection of the exterior of the skin at STA 1809.5 between stringers 
3R and 10R and detailed and HFEC inspections of the forward outer chord 
and surrounding structure between stringers 3R and 10R.
     Part 3 of the service bulletin specifies doing detailed 
and HFEC inspections of the end of the horizontal inner chord and 
surrounding structure on the left side of the STA 1809.5 bulkhead.
     Part 4 of the service bulletin specifies doing detailed 
and HFEC inspections of the end of the horizontal inner chord and 
surrounding structure on the right side of the STA 1809.5 bulkhead.
    The corrective actions include the following:
     Repairing any cracking found in the forward outer chord or 
in the horizontal inner chord. Repairing all cracking in a certain area 
terminates the repetitive inspections for that area only.
     Contacting the manufacturer for repair instructions if any 
cracking is found in the skin or in any structure other than the 
forward outer chord or horizontal inner chord.
    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

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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 ``Difference Between the Proposed AD and Service 
Bulletin.''

Difference Between the Proposed AD and Service Bulletin

    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.

Costs of Compliance

    There are about 903 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 405 airplanes of 
U.S. registry. The proposed actions would take about 12 work hours per 
airplane, at an average labor rate of $80 per work hour. Based on these 
figures, the estimated cost of the proposed AD for U.S. operators is 
$388,800, or $960 per airplane, per inspection cycle.

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-2006-24814; Directorate Identifier 2006-NM-
093-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by July 6, 
2006.

Affected ADs

    (b) None.

Applicability

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

Unsafe Condition

    (d) This AD results from cracks found in the forward outer chord 
and horizontal inner chord at station (STA) 1809.5. We are issuing 
this AD to detect and correct cracking in the bulkhead structure at 
STA 1809.5, which could result in failure of the bulkhead structure 
for carrying the flight loads of the horizontal stabilizer, and 
consequent loss of controllability 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 and Corrective Actions

    (f) Before the accumulation of 15,000 total flight cycles, or 
within 3,000 flight cycles after the effective date of this AD, 
whichever is later: Do the detailed and high frequency eddy current 
(HFEC) inspections for cracking as specified in Parts 1, 2, 3, and 4 
of the Accomplishment Instructions of Boeing Alert Service Bulletin 
767-53A0131, dated March 30, 2006; and do all corrective actions 
before further flight; by accomplishing all the actions specified in 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
767-53A0131, dated March 30, 2006, except as provided by paragraph 
(g) of this AD. Repeat the inspections thereafter at intervals not 
to exceed 6,000 flight cycles. Accomplishing the corrective action 
for the inspections specified in Part 1, 2, 3, or 4 of the service 
bulletin, as applicable, terminates the repetitive inspections for 
that area only.

Exception to Service Bulletin

    (g) If any cracking is found in the skin or in any structure 
other than the forward outer chord or horizontal inner chord, during 
any inspection required by this AD, and Boeing Alert Service 
Bulletin 767-53A0131, dated March 30, 2006, specifies to contact 
Boeing for appropriate action: Before further flight, repair the 
cracking using a method approved in accordance with the procedures 
specified in paragraph (h) of this AD.

Alternative Methods of Compliance (AMOCs)

    (h)(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.
    (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 May 15, 2006.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-7740 Filed 5-19-06; 8:45 am]
BILLING CODE 4910-13-P