Airworthiness Directives; Boeing Model 767 Airplanes, 25928-25930 [06-4055]

Download as PDF 25928 Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Rules and Regulations (2) Repeat the inspection required by paragraph (f) of this AD thereafter at intervals not to exceed 3,000 flight cycles. Optional Terminating Inspection (i) Accomplishment of the initial detailed inspection of the Section 46 lower lobe frames required by paragraph (f)(2) or (i)(2) of AD 2005–20–30 constitutes terminating action for the requirements of this AD only for airplanes identified in Boeing Alert Service Bulletin 747–53A2408, Revision 1, dated April 4, 2002, as Group 1 airplanes. Accomplishment of the initial detailed inspection of the Section 46 lower lobe frames required by paragraph (f) of AD 2006– 05–02 constitutes terminating action for the requirements of this AD only for airplanes identified in Boeing Alert Service Bulletin 747–53A2408, Revision 1, dated April 4, 2002, as Group 2 airplanes. sroberts on PROD1PC70 with RULES Alternative Methods of Compliance (AMOCs) (j)(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 § 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. (4) AMOCs approved previously in accordance with AD 99–07–12, are approved as AMOCs for the corresponding provisions of this AD. Material Incorporated by Reference (k) You must use Boeing Alert Service Bulletin 747–53A2408, dated April 25, 1996; or Boeing Alert Service Bulletin 747– 53A2408, Revision 1, dated April 4, 2002; as applicable; to perform the actions that are required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747–53A2408, Revision 1, dated April 4, 2002, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On May 5, 1999 (64 FR 15298, March 31, 1999), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747–53A2408, dated April 25, 1996. (3) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124– 2207, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or VerDate Aug<31>2005 18:14 May 02, 2006 Jkt 208001 at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to http://www. archives.gov/federal_register/code_of_federal _regulations/ibr_locations.html. Issued in Renton, Washington, on April 20, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–4054 Filed 5–2–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23762; Directorate Identifier 2005–NM–226–AD; Amendment 39–14580; AD 2006–09–09] RIN 2120–AA64 Airworthiness Directives; Boeing Model 767 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 767 airplanes. This AD requires 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 AD also provides for repairs, which are optional for airplanes on which no cracking is found, that terminate certain inspections. This 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 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. This AD becomes effective June 7, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of June 7, 2006. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket DATES: PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for service information identified in this 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: Examining the Docket You may examine the airworthiness directive (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 street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to all Boeing Model 767 airplanes. That NPRM was published in the Federal Register on February 2, 2006 (71 FR 5623). That NPRM proposed to 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. That NPRM also proposed to provide for repairs, which are optional for airplanes on which no cracking is found, that terminate certain inspections. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment received. The commenter, Boeing, supports the NPRM. Conclusion We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD as proposed. 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 AD. E:\FR\FM\03MYR1.SGM 03MYR1 Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Rules and Regulations 25929 ESTIMATED COSTS Action Part 1 Inspection, per inspection cycle. Part 2 Inspections, per inspection cycle. sroberts on PROD1PC70 with RULES Number of U.S.-registered airplanes Fleet cost $65 $325, per inspection cycle ........ 387 $125,775 per inspection cycle. 9 65 $585, per inspection cycle ........ 387 $226,395 per inspection cycle. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will 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 this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under 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 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, Incorporation by reference, Safety. 18:14 May 02, 2006 Cost per airplane 5 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. VerDate Aug<31>2005 Average labor rate per hour Work hours Jkt 208001 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 2006–09–09 Boeing: Amendment 39–14580. Docket No. FAA–2006–23762; Directorate Identifier 2005–NM–226–AD. Effective Date (a) This AD becomes effective June 7, 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 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 Special Attention Service Bulletin 767–53– 0118, dated September 8, 2005. Do the initial and repetitive Part 1 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 Boeing Special Attention Service Bulletin 767–53– 0118, dated September 8, 2005, terminates the 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 § 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 E:\FR\FM\03MYR1.SGM 03MYR1 25930 Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Rules and Regulations 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. Material Incorporated by Reference (j) You must use Boeing Special Attention Service Bulletin 767–53–0118, dated September 8, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to http://www. archives.gov/federal_register/code_of_ federal_regulations/ibr_locations.html. is present. This amendment is prompted by one incident in which a pilot lost T/ R pitch control of a helicopter while landing. The actions specified in this AD are intended to detect damage to the bearing, resulting in end play and prevent loss of T/R pitch control and subsequent loss of control of the helicopter. [Docket No. FAA–2006–24588; Directorate Identifier 2006–SW–07–AD; Amendment 39– 14581; AD 2006–09–10] Effective May 18, 2006. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of May 18, 2006. Comments for inclusion in the Rules Docket must be received on or before July 3, 2006. ADDRESSES: Use one of the following addresses to submit comments on this 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; or • 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. You may get the service information identified in this AD from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005, telephone (972) 641–3460, fax (972) 641–3527. RIN 2120–AA64 Examining the Docket Issued in Renton, Washington, on April 21, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–4055 Filed 5–2–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Airworthiness Directives; Eurocopter France Model SA–365 N1, AS–365 N2, N3, SA 366 G1, and EC–155B and B1 Helicopters Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. sroberts on PROD1PC70 with RULES AGENCY: SUMMARY: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) Model SA–365 N1, AS–365 N2, N3, SA 366 G1, and EC–155B and B1 helicopters. This action requires a one-time inspection for end play in the pitch control rod assembly double bearing (bearing) using the tail rotor (T/ R) hub control plate, and before further flight, replacing the bearing if end play VerDate Aug<31>2005 18:14 May 02, 2006 Jkt 208001 DATES: You may examine the docket that contains the AD, any comments, and other information on the Internet at http://dms.dot.gov, or in person at the Docket Management System (DMS) Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. FOR FURTHER INFORMATION CONTACT: Uday Garadi, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76193–0110, telephone (817) 222–5123, fax (817) 222–5961. PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 This amendment adopts a new AD for Eurocopter Model SA–365 N1, AS–365 N2, N3, SA 366 G1, and EC–155B and B1 helicopters. This action requires, within 50 hours time-in-service (TIS), a one-time inspection of the T/R hub control plate for end play in the bearing, and if end play is present, replacing the bearing before further flight. This amendment is prompted by one incident in which a pilot lost T/R pitch control of a helicopter while landing. The loss of the T/R pitch control was due to significant damage to the bearing of the control rod in the tail gearbox. This condition, if not detected, could result in loss of T/R pitch control and subsequent loss of control of the helicopter. The European Aviation Safety Agency (EASA) notified us that an unsafe condition may exist on Eurocopter France Model AS 365 N, SA 366, and EC 155 helicopters. EASA advises that the loss of pitch control is due to significant damage to the bearing of the control rod in the tail gearbox. Eurocopter has issued Alert Service Bulletin (ASB) No. 05.00.52, applicable to the Model 365 N1, N2, and N3 helicopters; ASB No. 05.36, applicable to Model 366 G1 helicopters; and ASB No. 05A013, applicable to Model EC– 155B and B1 helicopters, all dated February 15, 2006, and all of which specify a check at regular intervals to ensure there is no end play in the bearing of the T/R pitch control rod. EASA classified this ASB as mandatory and issued AD No. 2006–0051–E, dated February 20, 2006, to ensure the continued airworthiness of these helicopters in France. This AD does not require repetitive inspections because helicopters in this fleet do not normally accrue enough flight hours in a short period of time to justify issuing an immediately adopted final rule requiring repetitive inspections without allowing the public time to first comment on such a proposal. We may issue further AD action at a later date to propose repetitive 110-hours TIS inspections. This helicopter model is manufactured in France and is type certificated for operation in the United States under the provisions of Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral agreement. Under this agreement, EASA has kept the FAA informed of the situation described above. We have examined EASA’s findings, evaluated all pertinent information, and determined that AD action is necessary for products of this type design that are SUPPLEMENTARY INFORMATION: E:\FR\FM\03MYR1.SGM 03MYR1

Agencies

[Federal Register Volume 71, Number 85 (Wednesday, May 3, 2006)]
[Rules and Regulations]
[Pages 25928-25930]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-4055]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23762; Directorate Identifier 2005-NM-226-AD; 
Amendment 39-14580; AD 2006-09-09]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767 Airplanes

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

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Boeing Model 767 airplanes. This AD requires 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 AD also provides for repairs, which are optional for airplanes on 
which no cracking is found, that terminate certain inspections. This 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 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.

DATES: This AD becomes effective June 7, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of June 7, 2006.

ADDRESSES: You may examine the AD docket on the Internet at http://
dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for service information identified in this 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:

Examining the Docket

    You may examine the airworthiness directive (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 street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to all Boeing Model 767 
airplanes. That NPRM was published in the Federal Register on February 
2, 2006 (71 FR 5623). That NPRM proposed to 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. That NPRM also proposed to provide for repairs, which are 
optional for airplanes on which no cracking is found, that terminate 
certain inspections.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received. The 
commenter, Boeing, supports the NPRM.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD as proposed.

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 AD.

[[Page 25929]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                  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.
----------------------------------------------------------------------------------------------------------------

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 AD will not have federalism 
implications under Executive Order 13132. This AD will 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2006-09-09 Boeing: Amendment 39-14580. Docket No. FAA-2006-23762; 
Directorate Identifier 2005-NM-226-AD.

Effective Date

    (a) This AD becomes effective June 7, 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 1 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 Boeing Special Attention Service Bulletin 767-53-
0118, dated September 8, 2005, terminates the 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.
    (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

[[Page 25930]]

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.

Material Incorporated by Reference

    (j) You must use Boeing Special Attention Service Bulletin 767-
53-0118, dated September 8, 2005, to perform the actions that are 
required by this AD, unless the AD specifies otherwise. The Director 
of the Federal Register approved the incorporation by reference of 
this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for a copy of this service information. You 
may review copies at the Docket Management Facility, U.S. Department 
of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal_
register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on April 21, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-4055 Filed 5-2-06; 8:45 am]
BILLING CODE 4910-13-P