Airworthiness Directives; Boeing Model 707-300B, -300C, and -400 Series Airplanes, 39912-39914 [05-13435]

Download as PDF 39912 Federal Register / Vol. 70, No. 132 / Tuesday, July 12, 2005 / Rules and Regulations Model Fan Jet Falcon, Fan Jet Falcon Series C, D, E, and F airplanes; Model Mystere-Falcon 200 airplanes; and Model Mystere-Falcon 20–C5, 20–D5, 20–E5, and 20–F5 airplanes modified by Royal Air, Inc. It is not a rule of general applicability and affects only the applicant who applied to the FAA for approval of these features on the airplane. The substance of these special conditions has been subjected to the notice and comment procedure in several prior instances and has been derived without substantive change from those previously issued. Because a delay would significantly affect the certification of the airplane, which is imminent, the FAA has determined that prior public notice and comment are unnecessary and impracticable, and good cause exists for adopting these special conditions upon issuance. The FAA is requesting comments to allow interested persons to submit views that may not have been submitted in response to the prior opportunities for comment described above. List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the supplemental type certification basis for Dassault Model Fan Jet Falcon, Fan Jet Falcon Series C, D, E, and F airplanes; Model Mystere-Falcon 200 airplanes; and Model Mystere-Falcon 20–C5, 20– D5, 20–E5, and 20–F5 airplanes modified by Royal Air, Inc. 1. Protection from Unwanted Effects of High-Intensity Radiated Fields (HIRF). Each electrical and electronic system that performs critical functions must be designed and installed to ensure that the operation and operational capability of these systems to perform critical functions are not adversely affected when the airplane is exposed to highintensity radiated fields. 2. For the purpose of these special conditions, the following definition applies: Critical Functions: Functions whose failure would contribute to or cause a failure condition that would prevent the continued safe flight and landing of the airplane. VerDate jul<14>2003 14:34 Jul 11, 2005 Jkt 205001 Issued in Renton, Washington, on July 1, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–13658 Filed 7–11–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20725; Directorate Identifier 2003–NM–250–AD; Amendment 39–14183; AD 2005–14–06] RIN 2120–AA64 Airworthiness Directives; Boeing Model 707–300B, –300C, and –400 Series 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 707–300B, –300C, and –400 series airplanes. This AD requires repetitive inspections to detect cracked or broken hinge fitting assemblies of the inboard leading edge slats, and corrective action if necessary. This AD also provides as an option a preventive modification, which defers the repetitive inspections. In addition, this AD provides an option of replacing all hinge fitting assemblies with new, improved parts, which terminates the repetitive inspection requirements. This AD is prompted by results of a review to identify and implement procedures to ensure the continued structural airworthiness of aging transport category airplanes. We are issuing this AD to detect and correct fatigue cracking of the hinge fitting assembly of the inboard leading edge slats, which could result in reduced structural integrity of the slat system. This condition could result in loss of the inboard leading edge slat and could cause the flightcrew to lose control of the airplane. DATES: This AD becomes effective August 16, 2005. The incorporation by reference of a certain publication listed in the AD is approved by the Director of the Federal Register as of August 16, 2005. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. Docket: The AD docket contains the proposed AD, comments, and any final PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 disposition. You can examine the 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 U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Washington, DC. This docket number is FAA–2005–20725; the directorate identifier for this docket is 2003–NM– 250–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: The FAA proposed to amend 14 CFR part 39 with an AD for all Boeing Model 707–300B, –300C, and –400 series airplanes. That action, published in the Federal Register on March 30, 2005 (70 FR 16177), proposed to require repetitive inspections to detect cracked or broken hinge fitting assemblies of the inboard leading edge slats, and corrective action if necessary. That action also proposed an optional preventive modification, which defers the repetitive inspections. In addition, that action proposed an option of replacing all hinge fitting assemblies with new, improved parts, which terminates the repetitive inspection requirements. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment that has been submitted on the proposed AD. The commenter supports the proposed AD. Explanation of Change to Referenced Service Bulletin We have corrected the title of the service bulletin referred to in this AD to ‘‘Boeing 707/720 Service Bulletin 2982.’’ Clarification of Optional Preventative Modification We have revised the text of paragraph (i) of the AD to clarify that the optional preventative modification ‘‘defers the repetitive inspections required by paragraph (g) of this AD.’’ Conclusion We have carefully reviewed the available data, including the comment that has been submitted, and determined that air safety and the E:\FR\FM\12JYR1.SGM 12JYR1 Federal Register / Vol. 70, No. 132 / Tuesday, July 12, 2005 / Rules and Regulations public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance This AD affects about 189 Boeing Model 707–300B, –300C, and –400 39913 series airplanes worldwide. The following table provides the estimated costs for U.S. operators to comply with this AD. ESTIMATED COSTS Action Average labor rate per hour Work hours Dye Penetrant Inspection ......................... Preventive Modification (Optional) ............ Terminating Action (Optional) ................... 3 10 10 $65 65 65 Cost per airplane Parts (1) (1) $8,220 Number of U.S.-registered airplanes $195 (per inspection cycle) ...................... 650 (per inspection) ................................. 8,870 ......................................................... 16 16 16 1 None. 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. See the ADDRESSES section for VerDate jul<14>2003 14:34 Jul 11, 2005 Jkt 205001 a location to examine the regulatory evaluation. leading edge slat and could cause the flightcrew to lose control of the airplane. List of Subjects in 14 CFR Part 39 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. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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 FAA amends § 39.13 by adding the following new airworthiness directive (AD): I 2005–14–06 Boeing: Amendment 39–14183. Docket No. FAA–2005–20725; Directorate Identifier 2003–NM–250–AD. Effective Date (a) This AD becomes effective August 16, 2005. Affected ADs (b) None. Applicability (c) This AD applies to all Boeing Model 707–300B, –300C, and –400 series airplanes, certificated in any category. Unsafe Condition (d) This AD was prompted by results of a review to identify and implement procedures to ensure the continued structural airworthiness of aging transport category airplanes. We are issuing this AD to detect and correct fatigue cracking of the hinge fitting assembly of the inboard leading edge slats, which could result in reduced structural integrity of the slat system. This condition could result in loss of the inboard PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 Service Bulletin Reference (f) In this AD, the term ‘‘service bulletin’’ means the Accomplishment Instructions of Boeing 707/720 Service Bulletin 2982, Revision 2, dated October 7, 1977. Repetitive Inspections (g) Before the accumulation of 10,000 total flight hours, or within 1,500 flight hours after the effective date of this AD, whichever occurs later, do a dye penetrant inspection to detect cracked or broken hinge fitting assemblies of the inboard leading edge slats in accordance with Part I, ‘‘Inspection Data,’’ of the service bulletin. Repeat the inspection at intervals not to exceed 1,500 flight hours, except as provided by paragraph (i) or (k) of this AD. Corrective Action (h) If any crack or broken assembly is found during any inspection required by paragraph (g) of this AD, before further flight, do the action specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD. (1) Replace the hinge fitting assembly with a like serviceable part in accordance with Part I of the service bulletin. (2) Replace the hinge fitting assembly with a like serviceable part on which the preventative modification specified in paragraph (i) of this AD has been done, in accordance with Part II of the service bulletin. This replacement defers the repetitive inspection requirements of paragraph (g) of this AD for 15,000 flight hours for that hinge fitting assembly. (3) Replace the hinge fitting assembly with a new, improved part in accordance with Part III of the service bulletin. This replacement terminates the repetitive inspection requirements of paragraph (g) of this AD for that hinge fitting assembly. Note 1: For this AD, a ‘‘like serviceable part’’ is a serviceable part listed in the ‘‘Existing’’ part number column of Table II of the service bulletin that has been inspected E:\FR\FM\12JYR1.SGM 12JYR1 39914 Federal Register / Vol. 70, No. 132 / Tuesday, July 12, 2005 / Rules and Regulations and found to be crack free in accordance with paragraph (g) of this AD before installation. A ‘‘new part’’ is a part listed in the ‘‘Replacement’’ or ‘‘Optional’’ part number column of Table II of the service bulletin. Optional Preventative Modification (Defers Repetitive Inspections) (i) Doing a preventative modification by accomplishing all the procedures in Part II of the service bulletin, except as required by paragraph (j) of this AD, defers the repetitive inspections required by paragraph (g) of this AD. Within 15,000 flight hours after the preventive modification, do the repetitive inspections in paragraph (g) of this AD at intervals not to exceed 1,500 flight hours. (j) If any crack is found during the preventative modification specified in paragraph (i) of this AD, before further flight, do the action specified in paragraph (h) of this AD. Optional Terminating Action (k) Replacement of a hinge fitting assembly with a new, improved part terminates the repetitive inspection requirements of paragraph (g) of this AD for that assembly. Replacement of all hinge fitting assemblies with new, improved parts terminates the repetitive inspection requirements of this AD. The replacement must be done in accordance with Part III of the service bulletin. Actions Accomplished Using a Previous Issue of the Service Bulletin Page No. Revision level shown on page 1–6, 8, 12 ... 7, 9–11, 13– 27. 2 1 Oct. 7, 1977. June 29, 1970. The Director of the Federal Register approves the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service information, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go to 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 June 29, 2005. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–13435 Filed 7–11–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION (l) Actions accomplished before the effective date of this AD using Boeing 707/ 720 Service Bulletin 2982, Revision 1, dated June 29, 1970, are considered acceptable for compliance with the corresponding action in this AD. Federal Aviation Administration Alternative Methods of Compliance (AMOCs) Modification of Legal Description of the Class D and Class E Airspace; Topeka, Forbes Field, KS (m)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) An AMOC that provides an acceptable level of safety may be used for a preventive modification of hinge fitting assemblies of the inboard leading edge slat if it is approved by an Authorized Representative for the Boeing 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 (n) You must use Boeing 707/720 Service Bulletin 2982, Revision 2, dated October 7, 1977, to perform the actions that are required by this AD, unless the AD specifies otherwise. Boeing 707/720 Service Bulletin 2982, Revision 2, dated October 7, 1977, contains the following list of effective pages: VerDate jul<14>2003 14:34 Jul 11, 2005 Jkt 205001 14 CFR Part 71 [Docket No. FAA–205–21703; Airspace Docket No. 05–ACE–19] Federal Aviation Administration (FAA), DOT. ACTION: Direct final rule; request for comments. AGENCY: SUMMARY: An examination of controlled airspace for Topeka, Forbes Field, KS has revealed discrepancies in the airport reference point used in the legal description for the Class E airspace designated as a surface area. This action corrects that discrepancy by incorporating the current airport reference point in the Class E surface area for Topeka, Forbes Field, KS. This action also removes references to effective dates and times established in advance by a Notice to Airmen from the legal descriptions for Class D, Class E2 and Class E4 airspace. The effective dates and times are now continuously published in the Airport/Facility Directory. PO 00000 Frm 00010 Fmt 4700 This direct final rule is effective on 0901 UTC, October 27, 2005. Comments for inclusion in the Rules Docket must be received on or before July 29, 2005. ADDRESSES: Send comments on this proposal to the Docket Management System, U.S. Department of Transportation, Room Plaza 401, 400 Seventh Street, SW., Washington, DC 20590–0001. You must identify the docket number FAA–2005–21703/ Airspace Docket No. 05–ACE–19, at the beginning of your comments. You may also submit comments on the Internet at https://dms.dot.gov. You may review the public docket containing the proposal, any comments received, and any final disposition in person in the Dockets Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800–647–5527) is on the plaza level of the Department of Transportation NASSIF Building at the above address. FOR FURTHER INFORMATION CONTACT: Brenda Mumper, Air Traffic Division, Airspace Branch, ACE–520A, DOT Regional Headquarters Building, Federal Aviation Administration, 901 Locust, Kansas City, MO 64106; telephone: (816) 329–2524. SUPPLEMENTARY INFORMATION: This amendment to 14 CFR part 71 modifies the legal description for Class D airspace and Class E airspace designated as a surface area at Topeka, Forbes Field, KS to contain Instrument Flight Rule (IFR) operations in controlled airspace. The areas are depicted on appropriate aeronautical charts. Class D airspace areas are published in paragraph 5000 of FAA Order 7400.9M. Airspace Designation and Reporting Points, dated August 30, 2004, and effective September 16, 2004, which is incorporated by reference in 14 CFR 71.1. Class E airspace areas designated as surface areas are published in Paragraph 6002 and 6004 of the same FAA Order. The Class D and Class E airspace designations listed in this document will be published subsequently in the Order. DATES: Date shown on page Sfmt 4700 The Direct Final Rule Procedure The FAA anticipates that this regulation will not result in adverse or negative comment and, therefore, is issuing it as a direct final rule. Previous actions of this nature have not been controversial and have not resulted in adverse comments or objections. Unless a written adverse or negative comment, or a written notice of intent to submit an adverse or negative comment is received within the comment period, the regulation will become effective on E:\FR\FM\12JYR1.SGM 12JYR1

Agencies

[Federal Register Volume 70, Number 132 (Tuesday, July 12, 2005)]
[Rules and Regulations]
[Pages 39912-39914]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-13435]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20725; Directorate Identifier 2003-NM-250-AD; 
Amendment 39-14183; AD 2005-14-06]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 707-300B, -300C, and -400 
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 all 
Boeing Model 707-300B, -300C, and -400 series airplanes. This AD 
requires repetitive inspections to detect cracked or broken hinge 
fitting assemblies of the inboard leading edge slats, and corrective 
action if necessary. This AD also provides as an option a preventive 
modification, which defers the repetitive inspections. In addition, 
this AD provides an option of replacing all hinge fitting assemblies 
with new, improved parts, which terminates the repetitive inspection 
requirements. This AD is prompted by results of a review to identify 
and implement procedures to ensure the continued structural 
airworthiness of aging transport category airplanes. We are issuing 
this AD to detect and correct fatigue cracking of the hinge fitting 
assembly of the inboard leading edge slats, which could result in 
reduced structural integrity of the slat system. This condition could 
result in loss of the inboard leading edge slat and could cause the 
flightcrew to lose control of the airplane.

DATES: This AD becomes effective August 16, 2005.
    The incorporation by reference of a certain publication listed in 
the AD is approved by the Director of the Federal Register as of August 
16, 2005.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
    Docket: The AD docket contains the proposed AD, comments, and any 
final disposition. You can examine the 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 U.S. 
Department of Transportation, 400 Seventh Street SW., room PL-401, 
Washington, DC. This docket number is FAA-2005-20725; the directorate 
identifier for this docket is 2003-NM-250-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: The FAA proposed to amend 14 CFR part 39 
with an AD for all Boeing Model 707-300B, -300C, and -400 series 
airplanes. That action, published in the Federal Register on March 30, 
2005 (70 FR 16177), proposed to require repetitive inspections to 
detect cracked or broken hinge fitting assemblies of the inboard 
leading edge slats, and corrective action if necessary. That action 
also proposed an optional preventive modification, which defers the 
repetitive inspections. In addition, that action proposed an option of 
replacing all hinge fitting assemblies with new, improved parts, which 
terminates the repetitive inspection requirements.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment that has been 
submitted on the proposed AD. The commenter supports the proposed AD.

Explanation of Change to Referenced Service Bulletin

    We have corrected the title of the service bulletin referred to in 
this AD to ``Boeing 707/720 Service Bulletin 2982.''

Clarification of Optional Preventative Modification

    We have revised the text of paragraph (i) of the AD to clarify that 
the optional preventative modification ``defers the repetitive 
inspections required by paragraph (g) of this AD.''

Conclusion

    We have carefully reviewed the available data, including the 
comment that has been submitted, and determined that air safety and the

[[Page 39913]]

public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    This AD affects about 189 Boeing Model 707-300B, -300C, and -400 
series airplanes worldwide. The following table provides the estimated 
costs for U.S. operators to comply with this AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                      Number of
                                                     Average                                            U.S.-
               Action                  Work hours   labor rate     Parts       Cost per  airplane     registered
                                                     per hour                                         airplanes
----------------------------------------------------------------------------------------------------------------
Dye Penetrant Inspection............            3          $65        (\1\)  $195 (per inspection             16
                                                                              cycle).
Preventive Modification (Optional)..           10           65        (\1\)  650 (per inspection)..           16
Terminating Action (Optional).......           10           65       $8,220  8,870.................          16
----------------------------------------------------------------------------------------------------------------
\1\ None.

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. 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 FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2005-14-06 Boeing: Amendment 39-14183. Docket No. FAA-2005-20725; 
Directorate Identifier 2003-NM-250-AD.

Effective Date

    (a) This AD becomes effective August 16, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Boeing Model 707-300B, -300C, and -
400 series airplanes, certificated in any category.

Unsafe Condition

    (d) This AD was prompted by results of a review to identify and 
implement procedures to ensure the continued structural 
airworthiness of aging transport category airplanes. We are issuing 
this AD to detect and correct fatigue cracking of the hinge fitting 
assembly of the inboard leading edge slats, which could result in 
reduced structural integrity of the slat system. This condition 
could result in loss of the inboard leading edge slat and could 
cause the flightcrew to lose 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.

Service Bulletin Reference

    (f) In this AD, the term ``service bulletin'' means the 
Accomplishment Instructions of Boeing 707/720 Service Bulletin 2982, 
Revision 2, dated October 7, 1977.

Repetitive Inspections

    (g) Before the accumulation of 10,000 total flight hours, or 
within 1,500 flight hours after the effective date of this AD, 
whichever occurs later, do a dye penetrant inspection to detect 
cracked or broken hinge fitting assemblies of the inboard leading 
edge slats in accordance with Part I, ``Inspection Data,'' of the 
service bulletin. Repeat the inspection at intervals not to exceed 
1,500 flight hours, except as provided by paragraph (i) or (k) of 
this AD.

Corrective Action

    (h) If any crack or broken assembly is found during any 
inspection required by paragraph (g) of this AD, before further 
flight, do the action specified in paragraph (h)(1), (h)(2), or 
(h)(3) of this AD.
    (1) Replace the hinge fitting assembly with a like serviceable 
part in accordance with Part I of the service bulletin.
    (2) Replace the hinge fitting assembly with a like serviceable 
part on which the preventative modification specified in paragraph 
(i) of this AD has been done, in accordance with Part II of the 
service bulletin. This replacement defers the repetitive inspection 
requirements of paragraph (g) of this AD for 15,000 flight hours for 
that hinge fitting assembly.
    (3) Replace the hinge fitting assembly with a new, improved part 
in accordance with Part III of the service bulletin. This 
replacement terminates the repetitive inspection requirements of 
paragraph (g) of this AD for that hinge fitting assembly.

    Note 1: For this AD, a ``like serviceable part'' is a 
serviceable part listed in the ``Existing'' part number column of 
Table II of the service bulletin that has been inspected

[[Page 39914]]

and found to be crack free in accordance with paragraph (g) of this 
AD before installation. A ``new part'' is a part listed in the 
``Replacement'' or ``Optional'' part number column of Table II of 
the service bulletin.

Optional Preventative Modification (Defers Repetitive Inspections)

    (i) Doing a preventative modification by accomplishing all the 
procedures in Part II of the service bulletin, except as required by 
paragraph (j) of this AD, defers the repetitive inspections required 
by paragraph (g) of this AD. Within 15,000 flight hours after the 
preventive modification, do the repetitive inspections in paragraph 
(g) of this AD at intervals not to exceed 1,500 flight hours.
    (j) If any crack is found during the preventative modification 
specified in paragraph (i) of this AD, before further flight, do the 
action specified in paragraph (h) of this AD.

Optional Terminating Action

    (k) Replacement of a hinge fitting assembly with a new, improved 
part terminates the repetitive inspection requirements of paragraph 
(g) of this AD for that assembly. Replacement of all hinge fitting 
assemblies with new, improved parts terminates the repetitive 
inspection requirements of this AD. The replacement must be done in 
accordance with Part III of the service bulletin.

Actions Accomplished Using a Previous Issue of the Service Bulletin

    (l) Actions accomplished before the effective date of this AD 
using Boeing 707/720 Service Bulletin 2982, Revision 1, dated June 
29, 1970, are considered acceptable for compliance with the 
corresponding action in this AD.

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19.
    (2) An AMOC that provides an acceptable level of safety may be 
used for a preventive modification of hinge fitting assemblies of 
the inboard leading edge slat if it is approved by an Authorized 
Representative for the Boeing 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

    (n) You must use Boeing 707/720 Service Bulletin 2982, Revision 
2, dated October 7, 1977, to perform the actions that are required 
by this AD, unless the AD specifies otherwise. Boeing 707/720 
Service Bulletin 2982, Revision 2, dated October 7, 1977, contains 
the following list of effective pages:

------------------------------------------------------------------------
                                    Revision
                                      level
             Page No.               shown on       Date shown on page
                                      page
------------------------------------------------------------------------
1-6, 8, 12.......................           2  Oct. 7, 1977.
7, 9-11, 13-27...................           1  June 29, 1970.
------------------------------------------------------------------------

    The Director of the Federal Register approves the incorporation 
by reference of this document in accordance with 5 U.S.C. 552(a) and 
1 CFR part 51. To get copies of the service information, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 
98124-2207. To view the AD docket, go to the Docket Management 
Facility, U.S. Department of Transportation, 400 Seventh Street SW., 
room PL-401, Nassif Building, Washington, DC. To review copies of 
the service information, go to 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 June 29, 2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-13435 Filed 7-11-05; 8:45 am]
BILLING CODE 4910-13-P
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