Airworthiness Directives; Boeing Model 727, 727C, 727-100, 727-100C, and 727-200 Series Airplanes, 17696-17698 [06-3197]

Download as PDF 17696 Federal Register / Vol. 71, No. 67 / Friday, April 7, 2006 / Rules and Regulations Alternative Methods of Compliance (AMOCs) (g)(1) The Manager, New York Aircraft Certification Office, 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. Related Information (h) Canadian airworthiness directive CF– 2005–08R1, dated August 10, 2005, also addresses the subject of this AD. Material Incorporated by Reference (i) You must use Bombardier Service Bulletin 84–57–10, Revision ‘A,’ dated March 14, 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 Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, 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 https:// 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 https://www.archives.gov/federal_ register/code_of_federal_regulations/ibr_ locations.html. Issued in Renton, Washington, on March 24, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–3196 Filed 4–6–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23672; Directorate Identifier 2005–NM–237–AD; Amendment 39–14544; AD 2006–07–17] RIN 2120–AA64 wwhite on PROD1PC65 with RULES Airworthiness Directives; Boeing Model 727, 727C, 727–100, 727–100C, and 727–200 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: VerDate Aug<31>2005 16:05 Apr 06, 2006 Jkt 208001 SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing transport category airplanes. This AD requires determining if the terminal fittings of the spars of the wings are made of 7079 aluminum alloy material. For any positive finding, the AD requires doing repetitive inspections for cracks and corrosion of all exposed surfaces of the terminal fitting bores; doing repetitive inspections for cracks, corrosion, and other surface defects, of all exposed surfaces, including the flanges, of the terminal fitting; applying corrosion inhibiting compound to the terminal fittings; and repairing or replacing any cracked, corroded, or defective part with a new part. This AD also provides for an optional terminating action for the repetitive inspections. This AD results from reports of cracking of the terminal fittings of the spars of the wings. We are issuing this AD to detect and correct stress-corrosion cracking of the terminal fittings, which could result in the failure of one of the terminal fitting connections. Such a failure, combined with a similar failure of one of the other three terminal fittings, could result in the inability of the airplane structure to carry fail-safe loads, which could result in loss of structural integrity of the wing attachment points. DATES: This AD becomes effective May 12, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of May 12, 2006. ADDRESSES: You may examine the AD docket on the Internet at https:// 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: Daniel F. Kutz, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6456; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at https://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 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 (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 certain Boeing transport category airplanes. That NPRM was published in the Federal Register on January 25, 2006 (71 FR 4069). That NPRM proposed to require determining if the terminal fittings of the spars of the wings are made of 7079 aluminum alloy material. For any positive finding, the NPRM proposed to require doing repetitive inspections for cracks and corrosion of all exposed surfaces of the terminal fitting bores; doing repetitive inspections for cracks, corrosion, and other surface defects, of all exposed surfaces, including the flanges, of the terminal fitting; applying corrosion inhibiting compound to the terminal fittings; and repairing or replacing any cracked, corroded, or defective part with a new part. The NPRM also proposed to provide an optional terminating action for the repetitive 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. Interim Action This AD is considered to be interim action. The inspection reports that are required by this AD will enable the manufacturer to obtain better insight into the extent of the cracking and corrosion of the terminal fittings of the front and rear spars of the wings in the fleet, and to develop additional action if necessary to address the unsafe condition. If additional action is identified, we may consider further rulemaking. Costs of Compliance There are about 302 airplanes of the affected design in the worldwide fleet. This AD will affect about 157 airplanes of U.S. registry. The determination of forging number/material identification will take about 4 work hours per airplane, at an average labor rate of $65 E:\FR\FM\07APR1.SGM 07APR1 Federal Register / Vol. 71, No. 67 / Friday, April 7, 2006 / Rules and Regulations per work hour. Based on these figures, the estimated cost of the AD for U.S. operators is $40,820, or $260 per airplane. Accomplishing the fluorescent dye penetrant and detailed inspections, if required, will take about 16 work hours per airplane, at an average labor rate of $65 per work hour. Based on these figures, we estimate the cost of the inspections to be $1,040 per airplane, per inspection cycle. 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. 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. Adoption of the Amendment 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 Affected ADs (b) None. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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 2006–07–17 Boeing: Amendment 39–14544. Docket No. FAA–2006–23672; Directorate Identifier 2005–NM–237–AD. Effective Date (a) This AD becomes effective May 12, 2006. Applicability (c) This AD applies to Boeing Model 727, 727C, 727–100, 727–100C, and 727–200 series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 727–57A0185, Revision 1, dated November 3, 2005. Unsafe Condition (d) This AD results from reports of cracking of the terminal fittings of the front and rear spars of the wings. We are issuing this AD to detect and correct stress-corrosion cracking of the terminal fittings, which could result in the failure of one of the terminal fitting connections. Such a failure, combined with a similar failure of one of the other three terminal fittings, could result in the inability of the airplane structure to carry fail-safe 17697 loads, which could result in loss of structural integrity of the wing attachment points. 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. Determination of Type of Terminal Fittings, Repetitive Inspections, and Corrective Actions (f) Within 24 months after the effective date of this AD, determine if the terminal fittings of the front and rear spars of the wings are made of 7079 aluminum alloy material by either inspecting the forging number or doing a conductivity test, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727–57A0185, Revision 1, dated November 3, 2005. (1) If the forging number is that identified in Table 1 of this AD, or if the terminal fitting material is not made of 7079 aluminum alloy: No further action is required by this AD for that terminal fitting only. TABLE 1.—FORGING NUMBERS OF TERMINAL FITTINGS NOT MADE OF 7079 ALUMINUM ALLOY Forging number of terminal fittings Location (i) 65–16214–3 .......... (ii) 65–16213–3 ......... Rear spar of left wing. Front spar of left wing. Rear spar of right wing. Front spar of right wing. (iii) 65–16214–4 ........ (iv) 65–16213–4 ........ (2) If any forging number other than those identified in Table 1 of this AD is found, or if any forging material is made of 7079 aluminum alloy, or if the material cannot be determined: Within 24 months after the effective date of this AD, do the inspections specified in Table 2 of this AD and apply corrosion inhibiting compound (CIC) to the terminal fittings, and before further flight, repair or replace any cracked, corroded, or defective part found during the inspections. Repeat the inspections thereafter at intervals not to exceed 60 months for the first two repeat intervals, and then thereafter at intervals not to exceed 30 months. Do the inspections, application of CIC, and repair in accordance with the service bulletin, except as provided by paragraphs (h) and (i) of this AD. Do the replacement in accordance with paragraph (g) of this AD. TABLE 2.—INSPECTIONS For— Of— (i) A fluorescent dye penetrant inspection ......... wwhite on PROD1PC65 with RULES Do— Cracks and corrosion ....................................... (ii) A detailed inspection .................................... Cracks, corrosion, and other surface defects .. All exposed surfaces of the terminal fitting bores. All exposed surfaces, including the flanges, of the terminal fitting. VerDate Aug<31>2005 16:05 Apr 06, 2006 Jkt 208001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\07APR1.SGM 07APR1 17698 Federal Register / Vol. 71, No. 67 / Friday, April 7, 2006 / Rules and Regulations Optional Terminating Action (g) Replacement of any terminal fitting of the front and rear spars of the wings with a new terminal fitting not made of 7079 aluminum alloy, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, ends the repetitive inspections required by paragraph (f)(2) of this AD for that terminal fitting only. For the replacement to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager’s approval letter must specifically refer to this AD. Exception to Service Information (h) Where the service bulletin specifies to contact Boeing for appropriate action: Before further flight, repair the cracked, corroded, or defective part using a method approved in accordance with the procedures specified in paragraph (l) of this AD, or replace in accordance with paragraph (g) of this AD. (i) Although the note in paragraph 3.B.7. of the service bulletin specifies procedures for a fluorescent dye penetrant inspection of the body fitting bore and repair if necessary, those procedures are not required by this AD. Parts Installation (j) As of the effective date of this AD, no person may install any terminal fitting having forging number 65–16213–1/–2 or 65– 16214–1/–2, or install any terminal fitting material made of 7079 aluminum alloy, on any airplane. wwhite on PROD1PC65 with RULES Reporting (k) Submit a report of the findings (both positive and negative) of the initial inspection required by paragraph (f)(2) of this AD to Boeing Commercial Airplanes, Attention: Manager, Airline Support, P.O. Box 3707, Seattle, WA 98124–2207, at the applicable time specified in paragraph (k)(1) or (k)(2) of this AD. The report must include the operator’s name, inspection results, a detailed description of any discrepancies found, the airplane serial number, and the number of flight cycles and flight hours on the airplane. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120–0056. (1) If the inspection was done after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was accomplished prior to the effective date of this AD: Submit the report within 30 days after the effective date of this AD. Alternative Methods of Compliance (AMOCs) (l)(1) The Manager, Seattle 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. VerDate Aug<31>2005 16:05 Apr 06, 2006 Jkt 208001 (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. Material Incorporated by Reference (m) You must use Boeing Alert Service Bulletin 727–57A0185, Revision 1, dated November 3, 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 https://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 https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on March 24, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–3197 Filed 4–6–06; 8:45 am] BILLING CODE 4910–13–P of the interior of the internal elevator torque tube of each elevator control surface for oxidation and corrosion, and corrective actions. This AD results from corrosion in torque tubes of the elevators found during scheduled maintenance. We are issuing this AD to detect and correct corrosion in the torque tubes of the elevators, which could lead to an unbalanced elevator and result in reduced controllability of the airplane. DATES: This AD becomes effective May 12, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of May 12, 2006. ADDRESSES: You may examine the AD docket on the Internet at https:// 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 Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box 343—CEP 12.225, Sao Jose dos Campos—SP, Brazil, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Examining the Docket DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23674; Directorate Identifier 2005–NM–234–AD; Amendment 39–14545; AD 2006–07–18] RIN 2120–AA64 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–120, –120ER, –120FC, –120QC, and –120RT Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–120, –120ER, –120FC, –120QC, and –120RT airplanes. This AD requires a one-time inspection PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 You may examine the airworthiness directive (AD) docket on the Internet at https://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 certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–120, –120ER, –120FC, –120QC, and –120RT airplanes. That NPRM was published in the Federal Register on January 25, 2006 (71 FR 4075). That NPRM proposed to require a one-time inspection of the interior of the internal elevator torque tube of each elevator control surface for oxidation and corrosion, and corrective actions. E:\FR\FM\07APR1.SGM 07APR1

Agencies

[Federal Register Volume 71, Number 67 (Friday, April 7, 2006)]
[Unknown Section]
[Pages 17696-17698]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-3197]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23672; Directorate Identifier 2005-NM-237-AD; 
Amendment 39-14544; AD 2006-07-17]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727, 727C, 727-100, 727-
100C, and 727-200 Series Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Boeing transport category airplanes. This AD requires 
determining if the terminal fittings of the spars of the wings are made 
of 7079 aluminum alloy material. For any positive finding, the AD 
requires doing repetitive inspections for cracks and corrosion of all 
exposed surfaces of the terminal fitting bores; doing repetitive 
inspections for cracks, corrosion, and other surface defects, of all 
exposed surfaces, including the flanges, of the terminal fitting; 
applying corrosion inhibiting compound to the terminal fittings; and 
repairing or replacing any cracked, corroded, or defective part with a 
new part. This AD also provides for an optional terminating action for 
the repetitive inspections. This AD results from reports of cracking of 
the terminal fittings of the spars of the wings. We are issuing this AD 
to detect and correct stress-corrosion cracking of the terminal 
fittings, which could result in the failure of one of the terminal 
fitting connections. Such a failure, combined with a similar failure of 
one of the other three terminal fittings, could result in the inability 
of the airplane structure to carry fail-safe loads, which could result 
in loss of structural integrity of the wing attachment points.

DATES: This AD becomes effective May 12, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of May 12, 2006.

ADDRESSES: You may examine the AD docket on the Internet at https://
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: Daniel F. Kutz, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6456; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at https://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 certain Boeing 
transport category airplanes. That NPRM was published in the Federal 
Register on January 25, 2006 (71 FR 4069). That NPRM proposed to 
require determining if the terminal fittings of the spars of the wings 
are made of 7079 aluminum alloy material. For any positive finding, the 
NPRM proposed to require doing repetitive inspections for cracks and 
corrosion of all exposed surfaces of the terminal fitting bores; doing 
repetitive inspections for cracks, corrosion, and other surface 
defects, of all exposed surfaces, including the flanges, of the 
terminal fitting; applying corrosion inhibiting compound to the 
terminal fittings; and repairing or replacing any cracked, corroded, or 
defective part with a new part. The NPRM also proposed to provide an 
optional terminating action for the repetitive 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.

Interim Action

    This AD is considered to be interim action. The inspection reports 
that are required by this AD will enable the manufacturer to obtain 
better insight into the extent of the cracking and corrosion of the 
terminal fittings of the front and rear spars of the wings in the 
fleet, and to develop additional action if necessary to address the 
unsafe condition. If additional action is identified, we may consider 
further rulemaking.

Costs of Compliance

    There are about 302 airplanes of the affected design in the 
worldwide fleet. This AD will affect about 157 airplanes of U.S. 
registry. The determination of forging number/material identification 
will take about 4 work hours per airplane, at an average labor rate of 
$65

[[Page 17697]]

per work hour. Based on these figures, the estimated cost of the AD for 
U.S. operators is $40,820, or $260 per airplane.
    Accomplishing the fluorescent dye penetrant and detailed 
inspections, if required, will take about 16 work hours per airplane, 
at an average labor rate of $65 per work hour. Based on these figures, 
we estimate the cost of the inspections to be $1,040 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 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):

2006-07-17 Boeing: Amendment 39-14544. Docket No. FAA-2006-23672; 
Directorate Identifier 2005-NM-237-AD.

Effective Date

    (a) This AD becomes effective May 12, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 727, 727C, 727-100, 727-
100C, and 727-200 series airplanes, certificated in any category; as 
identified in Boeing Alert Service Bulletin 727-57A0185, Revision 1, 
dated November 3, 2005.

Unsafe Condition

    (d) This AD results from reports of cracking of the terminal 
fittings of the front and rear spars of the wings. We are issuing 
this AD to detect and correct stress-corrosion cracking of the 
terminal fittings, which could result in the failure of one of the 
terminal fitting connections. Such a failure, combined with a 
similar failure of one of the other three terminal fittings, could 
result in the inability of the airplane structure to carry fail-safe 
loads, which could result in loss of structural integrity of the 
wing attachment points.

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.
    Determination of Type of Terminal Fittings, Repetitive 
Inspections, and Corrective Actions
    (f) Within 24 months after the effective date of this AD, 
determine if the terminal fittings of the front and rear spars of 
the wings are made of 7079 aluminum alloy material by either 
inspecting the forging number or doing a conductivity test, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 727-57A0185, Revision 1, dated November 3, 2005.
    (1) If the forging number is that identified in Table 1 of this 
AD, or if the terminal fitting material is not made of 7079 aluminum 
alloy: No further action is required by this AD for that terminal 
fitting only.

Table 1.--Forging Numbers of Terminal Fittings Not Made of 7079 Aluminum
                                  Alloy
------------------------------------------------------------------------
   Forging number of  terminal fittings               Location
------------------------------------------------------------------------
(i) 65-16214-3............................  Rear spar of left wing.
(ii) 65-16213-3...........................  Front spar of left wing.
(iii) 65-16214-4..........................  Rear spar of right wing.
(iv) 65-16213-4...........................  Front spar of right wing.
------------------------------------------------------------------------

    (2) If any forging number other than those identified in Table 1 
of this AD is found, or if any forging material is made of 7079 
aluminum alloy, or if the material cannot be determined: Within 24 
months after the effective date of this AD, do the inspections 
specified in Table 2 of this AD and apply corrosion inhibiting 
compound (CIC) to the terminal fittings, and before further flight, 
repair or replace any cracked, corroded, or defective part found 
during the inspections. Repeat the inspections thereafter at 
intervals not to exceed 60 months for the first two repeat 
intervals, and then thereafter at intervals not to exceed 30 months. 
Do the inspections, application of CIC, and repair in accordance 
with the service bulletin, except as provided by paragraphs (h) and 
(i) of this AD. Do the replacement in accordance with paragraph (g) 
of this AD.

                          Table 2.--Inspections
------------------------------------------------------------------------
              Do--                       For--               Of--
------------------------------------------------------------------------
(i) A fluorescent dye penetrant   Cracks and          All exposed
 inspection.                       corrosion.          surfaces of the
                                                       terminal fitting
                                                       bores.
(ii) A detailed inspection......  Cracks, corrosion,  All exposed
                                   and other surface   surfaces,
                                   defects.            including the
                                                       flanges, of the
                                                       terminal fitting.
------------------------------------------------------------------------


[[Page 17698]]

Optional Terminating Action

    (g) Replacement of any terminal fitting of the front and rear 
spars of the wings with a new terminal fitting not made of 7079 
aluminum alloy, in accordance with a method approved by the Manager, 
Seattle Aircraft Certification Office (ACO), FAA, ends the 
repetitive inspections required by paragraph (f)(2) of this AD for 
that terminal fitting only. For the replacement to be approved by 
the Manager, Seattle ACO, as required by this paragraph, the 
Manager's approval letter must specifically refer to this AD.

Exception to Service Information

    (h) Where the service bulletin specifies to contact Boeing for 
appropriate action: Before further flight, repair the cracked, 
corroded, or defective part using a method approved in accordance 
with the procedures specified in paragraph (l) of this AD, or 
replace in accordance with paragraph (g) of this AD.
    (i) Although the note in paragraph 3.B.7. of the service 
bulletin specifies procedures for a fluorescent dye penetrant 
inspection of the body fitting bore and repair if necessary, those 
procedures are not required by this AD.

Parts Installation

    (j) As of the effective date of this AD, no person may install 
any terminal fitting having forging number 65-16213-1/-2 or 65-
16214-1/-2, or install any terminal fitting material made of 7079 
aluminum alloy, on any airplane.

Reporting

    (k) Submit a report of the findings (both positive and negative) 
of the initial inspection required by paragraph (f)(2) of this AD to 
Boeing Commercial Airplanes, Attention: Manager, Airline Support, 
P.O. Box 3707, Seattle, WA 98124-2207, at the applicable time 
specified in paragraph (k)(1) or (k)(2) of this AD. The report must 
include the operator's name, inspection results, a detailed 
description of any discrepancies found, the airplane serial number, 
and the number of flight cycles and flight hours on the airplane. 
Under the provisions of the Paperwork Reduction Act of 1980 (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements contained in this 
AD and has assigned OMB Control Number 2120-0056.
    (1) If the inspection was done after the effective date of this 
AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was accomplished prior to the effective 
date of this AD: Submit the report within 30 days after the 
effective date of this AD.

Alternative Methods of Compliance (AMOCs)

    (l)(1) The Manager, Seattle 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.

Material Incorporated by Reference

    (m) You must use Boeing Alert Service Bulletin 727-57A0185, 
Revision 1, dated November 3, 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 https://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 https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on March 24, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-3197 Filed 4-6-06; 8:45 am]
BILLING CODE 4910-13-P
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